SOM 2014 Bhopal

For 2014 (IES, GATE & PSUs)

Strength of Materials

Contents Chapter – 1: Stress and Strain

Chapter - 2 : Principal Stress and Strain

Chapter - 3 : Moment of Inertia and Centroid

Chapter - 4 : Bending Moment and Shear

Force Diagram

Chapter - 5 : Deflection of Beam

Chapter - 6 : Bending Stress in Beam

Chapter - 7 : Shear Stress in Beam

Chapter - 8 : Fixed and Continuous Beam

Chapter - 9 : Torsion

Chapter-10 : Thin Cylinder

Chapter-11 : Thick Cylinder

Chapter-12 : Spring

Chapter-13 : Theories of Column

Chapter-14 : Strain Energy Method

Chapter-15 : Theories of Failure

Chapter-16 : Riveted and Welded Joint

S K Mondal

S K Mondal IES Officer (Railway), GATE topper, NTPC ET-2003 batch, 12 years teaching experienced, Author of Hydro Power Familiarization (NTPC Ltd)

Page 1 of 454 Bhopal

Note “Asked Objective Questions” is the total collection of questions from:-

22 yrs IES (2013-1992) [Engineering Service Examination]

22 yrs. GATE (2013-1992) [Mechanical Engineering]

11 yrs. GATE (2013-2003) [Civil Engineering]

and 14 yrs. IAS (Prelim.) [Civil Service Preliminary]

Copyright © 2007 S K Mondal

Every effort has been made to see that there are no errors (typographical or otherwise) in the

material presented. However, it is still possible that there are a few errors (serious or

otherwise). I would be thankful to the readers if they are brought to my attention at the

following e-mail address: [email protected]

S K Mondal


1. Stress and Strain Theory at a Glance (for IES, GATE, PSU) 1.1 Stress (σ) When a material is subjected to an external force, a resisting force is set up within the component. The

internal resistance force per unit area acting on a material or intensity of the forces distributed over a given

section is called the stress at a point.

• It uses original cross section area of the specimen and also known as engineering stress or

conventional stress.

Therefore, PA

σ =

• P is expressed in Newton (N) and A, original area, in square meters (m2), the stress σ will be

expresses in N/ m2. This unit is called Pascal (Pa).

• As Pascal is a small quantity, in practice, multiples of this unit is used.

1 kPa = 103 Pa = 103 N/ m2 (kPa = Kilo Pascal)

1 MPa = 106 Pa = 106 N/ m2 = 1 N/mm2 (MPa = Mega Pascal) 1 GPa = 109 Pa = 109 N/ m2 (GPa = Giga Pascal)

Let us take an example: A rod 10 mm ×10 mm cross-section is carrying an axial tensile load 10 kN. In

this rod the tensile stress developed is given by

( )( )

32

210 10 10 100N/mm 100MPa

10 10 100tP kN NA mm mm mm

σ×

= = = = =×

• The resultant of the internal forces for an axially loaded member is

normal to a section cut perpendicular to the member axis.

• The force intensity on the shown section is defined as the normal stress.

0lim and avgA

F PA A

σ σΔ →

Δ= =

Δ

• Tensile stress (σt) If σ > 0 the stress is tensile. i.e. The fibres of the component

tend to elongate due to the external force. A member

subjected to an external force tensile P and tensile stress distribution due to the force is shown in the given figure.


Chapter-1 Stress and Strain S K Mondal’s

• Compressive stress (σc) If σ < 0 the stress is compressive. i.e. The fibres of the

component tend to shorten due to the external force. A

member subjected to an external compressive force P and

compressive stress distribution due to the force is shown in

the given figure.

• Shear stress (τ ) When forces are transmitted from one part of a body to other, the stresses

developed in a plane parallel to the applied force are the shear stress. Shear

stress acts parallel to plane of interest. Forces P is applied

transversely to the member AB as shown. The corresponding

internal forces act in the plane of section C and are called shearing

forces. The corresponding average shear stress ( ) PArea

τ =

1.2 Strain (ε) The displacement per unit length (dimensionless) is

known as strain.

• Tensile strain (ε t)

The elongation per unit length as shown in the figure is known as tensile strain.

εt = ΔL/ Lo

It is engineering strain or conventional strain.

Here we divide the elongation to original length

not actual length (Lo + Δ L)

Let us take an example: A rod 100 mm in original length. When we apply an axial tensile load 10 kN the

final length of the rod after application of the load is 100.1 mm. So in this rod tensile strain is developed and is given by

( ) 100.1 100 0.1 0.001 (Dimensionless)Tensile100 100

ot

o o

L LL mm mm mmL L mm mm

ε−Δ −

= = = = =

• Compressive strain (ε c) If the applied force is compressive then the reduction of length per unit length is known as

compressive strain. It is negative. Then εc = (-∆L)/ Lo Let us take an example: A rod 100 mm in original length. When we apply an axial compressive load 10

kN the final length of the rod after application of the load is 99 mm. So in this rod a compressive strain is

developed and is given by



( ) 99 100 1 0.01 (Dimensionless)compressive100 100

oc

o o

L LL mm mm mmL L mm mm

ε−Δ − −

= = = = =−

• Shear Strain (γ ): When a

force P is applied tangentially to

the element shown. Its edge displaced to dotted line. Where

δ is the lateral displacement of

the upper face of the element relative to the lower face and L is the distance between these faces.

Then the shear strain is ( )Lδ

γ =

Let us take an example: A block 100 mm × 100 mm base and 10 mm height. When we apply a tangential

force 10 kN to the upper edge it is displaced 1 mm relative to lower face.

Then the direct shear stress in the element

(τ ) 3

210 10 10 1 N/mm 1 MPa100 100 100 100

kN Nmm mm mm mm

×= = = =

× ×

And shear strain in the element (γ ) = 1 0.110

mmmm

= = Dimensionless

1.3 True stress and True Strain

The true stress is defined as the ratio of the load to the cross section area at any instant.

( ) loadInstantaneous areaTσ = ( )1σ ε= +

Where σ and ε is the engineering stress and engineering strain respectively.

• True strain

( ) ( )ln ln 1 ln 2lno

Lo o

ToL

A ddl Ll L A d

ε ε⎛ ⎞ ⎛ ⎞ ⎛ ⎞⎟⎜ ⎟ ⎟⎜ ⎜⎟= = = + = =⎟ ⎟⎜ ⎜ ⎜⎟ ⎟ ⎟⎜ ⎟ ⎟⎜ ⎜⎟⎜ ⎝ ⎠ ⎝ ⎠⎝ ⎠∫

or engineering strain (ε ) = Teε -1

The volume of the specimen is assumed to be constant during plastic deformation. [

o oA L AL=∵ ] It is valid till the neck formation.

• Comparison of engineering and the true stress-strain curves shown below



• The true stress-strain curve is also known as the flow curve.

• True stress-strain curve gives a true indication of deformation characteristics because it is based on the instantaneous dimension of the specimen.

• In engineering stress-strain curve, stress drops down after necking since it is based on the original area.

• In true stress-strain curve, the stress however increases after necking since the cross-sectional area of the specimen decreases rapidly after necking.

• The flow curve of many metals in the region of uniform plastic deformation can be expressed by

the simple power law.

σT = K(εT)n Where K is the strength coefficient

n is the strain hardening exponent

n = 0 perfectly plastic solid

n = 1 elastic solid

For most metals, 0.1< n < 0.5

• Relation between the ultimate tensile strength and true stress at maximum load

The ultimate tensile strength ( ) maxu

o

PA

σ =

The true stress at maximum load ( ) maxu T

PA

σ =

And true strain at maximum load ( ) ln oT

AA

ε⎛ ⎞⎟⎜= ⎟⎜ ⎟⎟⎜⎝ ⎠

or ToAe

Aε=

Eliminating Pmax we get , ( ) max max Tou uT

o

P P A eA A A

εσ σ= = × =

Where Pmax = maximum force and Ao = Original cross section area

A = Instantaneous cross section area Let us take two examples: (I.) Only elongation no neck formation In the tension test of a rod shown initially it was Ao = 50 mm2 and Lo = 100 mm. After the application of load it’s A = 40 mm2 and L = 125 mm. Determine the true strain using changes in both length and area.

Answer: First of all we have to check that does the member forms neck or not? For that check =o oA L AL

or not? Here 50 × 100 = 40 × 125 so no neck formation is there. Therefore true strain

(If no neck formation occurs both area and gauge length can be used for a strain calculation.)



( ) 125ln 0.223100

o

L

TL

dll

ε⎛ ⎞⎟⎜= = =⎟⎜ ⎟⎟⎜⎝ ⎠∫

( ) 50ln ln 0.22340

oT

AA

ε⎛ ⎞ ⎛ ⎞⎟ ⎟⎜ ⎜= = =⎟ ⎟⎜ ⎜⎟ ⎟⎟⎜⎜ ⎟ ⎝ ⎠⎝ ⎠

(II.) Elongation with neck formation A ductile material is tested such and necking occurs then the final gauge length is L=140 mm and the final minimum cross sectional area is A = 35 mm2. Though the rod shown initially it was Ao = 50 mm2 and Lo = 100 mm. Determine the true strain using changes in both length and area.

Answer: First of all we have to check that does the member forms neck or not? For that check =o oA L AL

or not? Here AoLo = 50 × 100 = 5000 mm3 and AL=35 × 140 = 4200 mm3. So neck formation is there. Note here AoLo > AL. Therefore true strain

( ) 50ln ln 0.35735

oT

AA

ε⎛ ⎞ ⎛ ⎞⎟ ⎟⎜ ⎜= = =⎟ ⎟⎜ ⎜⎟ ⎟⎟⎜⎜ ⎟ ⎝ ⎠⎝ ⎠

But not ( ) 140ln 0.336100

o

L

TL

dll

ε⎛ ⎞⎟⎜= = =⎟⎜ ⎟⎟⎜⎝ ⎠∫ (it is wrong)

(After necking, gauge length gives error but area and diameter can be used for the calculation of true strain at fracture and before fracture also.)

1.4 Hook’s law

According to Hook’s law the stress is directly proportional to strain i.e. normal stress (σ) α normal strain

(ε) and shearing stress ( τ ) α shearing strain ( γ ).

σ = Eε and Gτ γ=

The co-efficient E is called the modulus of elasticity i.e. its resistance to elastic strain. The co-efficient G is

called the shear modulus of elasticity or modulus of rigidity.

1.5 Volumetric strain( )vε

A relationship similar to that for length changes holds for three-dimensional (volume) change. For

volumetric strain,( )vε , the relationship is ( )vε = (V-V0)/V0 or ( )vε = ΔV/V0PK

=

• Where V is the final volume, V0 is the original volume, and ΔV is the volume change.

• Volumetric strain is a ratio of values with the same units, so it also is a dimensionless quantity.

• ΔV/V= volumetric strain = εx +εy + εz = ε1 +ε2 + ε3



• Dilation: The hydrostatic component of the total stress contributes to deformation by changing the area (or volume, in three dimensions) of an object. Area or volume change is called dilation and is

positive or negative, as the volume increases or decreases, respectively. peK

= Where p is pressure.

1.6 Young’s modulus or Modulus of elasticity (E) = PL σ=Aδ ∈

1.7 Modulus of rigidity or Shear modulus of elasticity (G) = τγ

= PLAδ

=

1.8 Bulk Modulus or Volume modulus of elasticity (K) = p pv R

v R

Δ Δ− =Δ Δ

1.10 Relationship between the elastic constants E, G, K, µ

( ) ( ) 9KGE 2G 1 3K 1 23K G

μ μ= + = − =+ [VIMP]

Where K = Bulk Modulus, μ = Poisson’s Ratio, E= Young’s modulus, G= Modulus of rigidity

• For a linearly elastic, isotropic and homogeneous material, the number of elastic constants required to relate stress and strain is two. i.e. any two of the four must be known.

• If the material is non-isotropic (i.e. anisotropic), then the elastic modulii will vary with additional stresses appearing since there is a coupling between shear stresses and normal stresses for an anisotropic material.

Let us take an example: The modulus of elasticity and rigidity of a material are 200 GPa and 80 GPa, respectively. Find all other elastic modulus.

Answer: Using the relation ( ) ( )μ μ= + = − =+

9KGE 2G 1 3K 1 23K G

we may find all other elastic modulus easily

Poisson’s Ratio μ μ μ+ = ⇒ = − = − =×

E E 200( ) : 1 1 1 0.252G 2G 2 80

Bulk Modulus (K) : ( ) ( )μ μ

= ⇒ = = =− − − ×E E 2003K K 133.33GPa

1 2 3 1 2 3 1 2 0.25

1.11 Poisson’s Ratio (µ)

= Transverse strain or lateral strainLongitudinal strain

= y

x

−∈∈

(Under unidirectional stress in x-direction)

• The theory of isotropic elasticity allows Poisson's ratios in the range from -1 to 1/2.

• Poisson's ratio in various materials Material Poisson's ratio Material Poisson's ratio Steel 0.25 – 0.33 Rubber 0.48 – 0.5C.I 0.23 – 0.27 Cork Nearly zeroConcrete 0.2 Novel foam negative



• We use cork in a bottle as the cork easily inserted and removed, yet it also withstand the pressure from within the bottle. Cork with a Poisson's ratio of nearly zero, is ideal in this application.

• If a piece of material neither expands nor contracts in volume when subjected to stress, then the Poisson’s ratio must be 1/2.

1.12 For bi-axial stretching of sheet

11 o

1

22

2

ln L length

ln L -Final length

f

o

ff

o

LOriginal

L

LL

⎛ ⎞∈ = −⎜ ⎟

⎝ ⎠⎛ ⎞

∈ = ⎜ ⎟⎝ ⎠

Final thickness (tf) = 1 2

thickness(t )oInitiale e∈ ∈×

1.13 Elongation • A prismatic bar loaded in tension by an axial force P

For a prismatic bar loaded in tension by an axial force P. The elongation of the bar can be determined as

δ = PLAE

Let us take an example: A Mild Steel wire 5 mm in diameter and 1 m long. If the wire is subjected to an

axial tensile load 10 kN find its extension of the rod. (E = 200 GPa)

Answer: ( )δ =We know that PLAE

( )ππ −

= = ×=

×= = = ×

222 5 2

Here given, Force (P) 10 10 1000NLength(L) 1 m

0.005Area(A) m 1.963 10 m

4 4

kN

d

( )( ) ( )δ

−

−

= = ×× ×

= =× × ×

= × =

9 2

5 9

3

Modulous of Elasticity ( ) 200 200 10 N/m10 1000 1

Therefore Elongation( ) m1.963 10 200 10

2.55 10 m 2.55 mm

E GPaPLAE

• Elongation of composite body Elongation of a bar of varying cross section A1, A2,----------,An of lengths l1, l2,--------ln respectively.

31 2 n

1 2 3

δ⎡ ⎤

= + + − − − − − − − +⎢ ⎥⎣ ⎦n

ll l lPE A A A A

Let us take an example: A composite rod is 1000 mm long, its two ends are 40 mm2 and 30 mm2 in area

and length are 300 mm and 200 mm respectively. The middle portion of the rod is 20 mm2 in area and 500

mm long. If the rod is subjected to an axial tensile load of 1000 N, find its total elongation. (E = 200 GPa).



Answer: Consider the following figure

Given, Load (P) =1000 N

Area; (A1) = 40 mm2, A2 = 20 mm2, A3 = 30 mm2

Length; (l1) = 300 mm, l2 = 500 mm, l3 = 200 mm E = 200 GPa = 200× 109 N/m2 = 200× 103 N/mm2

Therefore Total extension of the rod

δ⎡ ⎤

= + +⎢ ⎥⎣ ⎦

⎡ ⎤= × + +⎢ ⎥× ⎣ ⎦=

31 2

1 2 3

3 2 2 2 21000 300 500 200

200 10 / 40 20 300.196mm

ll lPE A A A

N mm mm mmN mm mm mm mm

• Elongation of a tapered body Elongation of a tapering rod of length ‘L’ due to load ‘P’ at the end

1 2

4PLδ=Edπ d (d1 and d2 are the diameters of smaller & larger ends)

You may remember this in this way,

1 2

PL PLδ= . .EAE

4π⎛ ⎞⎜ ⎟⎝ ⎠

eq

i ed d

Let us take an example: A round bar, of length L, tapers uniformly from small diameter d1 at one end to

bigger diameter d2 at the other end. Show that the extension produced by a tensile axial load P is

( )1 2

4PLδ =Eπd d

.

If d2 = 2d1, compare this extension with that of a uniform cylindrical bar having a diameter equal to the mean diameter of the tapered bar.

Answer: Consider the figure below d1 be the radius at the smaller end. Then at a X cross section XX

located at a distance × from the smaller end, the value of diameter ‘dx’ is equal to



( )

( )

⎛ ⎞= + −⎜ ⎟⎝ ⎠

= + −

−= + = ×

1 2 1

1 2 1

2 11

1

2 2 2 2

11

x

x

d d d dxL

xor d d d dL

d dd kx Where kL d

( )( ){ }

δπ π

= = =⎛ ⎞ +×⎜ ⎟⎝ ⎠

x x

x

221

We now taking a small strip of diameter 'd 'and length 'd 'at section .Elongation of this section 'd ' length

. 4 .. 1

4x

XX

PL P dx P dxdAE d d kx EE

( )( )

δ δπ

π

=

=

= =+

=

∫ ∫ 220 1

1 2

Therefore total elongation of the taper bar4

14

x L

x

P dxdEd kxPL

E d d

Comparison: Case-I: Where d2 = 2d1

Elongation ( )δπ π

= =× 2

1 1 1

4 22I

PL PLEd d Ed

Case –II: Where we use Mean diameter

( )δπ

π

+ += = =

= =⎛ ⎞⎜ ⎟⎝ ⎠

=

= =

1 2 1 11

2

1

21

2 32 2 2

.Elongation of such bar3 .

4 216

9Extension of taper bar 2 9

16Extension of uniform bar 89

m

II

d d d dd d

PL P LAE

d E

PLEd



• Elongation of a body due to its self weight (i) Elongation of a uniform rod of length ‘L’ due to its own weight ‘W’

WLδ=2AE

The deformation of a bar under its own weight as compared to that when subjected to a

direct axial load equal to its own weight will be half.

(ii) Total extension produced in rod of length ‘L’ due to its own weight ‘ω ’ per with

length. 2

δ=2EAωL

(iii) Elongation of a conical bar due to its self weight

2

max

δ=6E 2

ρ =gL WLA E

1.14 Structural members or machines must be designed such that the working stresses are less than the

ultimate strength of the material.

( )

11

Working stress n=1.5 to 2factor of safety

n 2 to 3

Proof stress

yw

ult

pp

n

n

n

σσ

σ

σσ

⎫= ⎪

⎪⎬⎪= = ⎪⎭

= =

1.15 Factor of Safety: (n) = y p ult

w

or orσ σ σσ

1.16 Thermal or Temperature stress and strain

• When a material undergoes a change in temperature, it either elongates or contracts depending

upon whether temperature is increased or decreased of the material.

• If the elongation or contraction is not restricted, i. e. free then the material does not experience

any stress despite the fact that it undergoes a strain.

• The strain due to temperature change is called thermal strain and is expressed as,

( )Tε α= Δ

• Where α is co-efficient of thermal expansion, a material property, and ΔT is the change in

temperature.

• The free expansion or contraction of materials, when restrained induces stress in the material

and it is referred to as thermal stress.



( )σ α= Δt E T Where, E = Modulus of elasticity

• Thermal stress produces the same effect in the material similar to that of mechanical stress. A

compressive stress will produce in the material with increase in temperature and the stress

developed is tensile stress with decrease in temperature.

Let us take an example: A rod consists of two parts that are made of steel and copper as shown in figure

below. The elastic modulus and coefficient of thermal expansion for steel are 200 GPa and 11.7 × 10-6 per °C

respectively and for copper 70 GPa and 21.6 × 10-6 per °C respectively. If the temperature of the rod is

raised by 50°C, determine the forces and stresses acting on the rod.

Answer: If we allow this rod to freely expand then free expansion

( )( ) ( )

( )

δ α− −

= Δ

= × × × + × × ×

=

6 611.7 10 50 500 21.6 10 50 750

1.1025 mm Compressive

T T L

But according to diagram only free expansion is 0.4 mm.

Therefore restrained deflection of rod =1.1025 mm – 0.4 mm = 0.7025 mm Let us assume the force required to make their elongation vanish be P which is the reaction force at the

ends.

( ) ( ) ( ) ( )

δ

π π

⎛ ⎞ ⎛ ⎞= +⎜ ⎟ ⎜ ⎟⎝ ⎠ ⎝ ⎠

× ×= +⎧ ⎫ ⎧ ⎫× × × × × ×⎨ ⎬ ⎨ ⎬⎩ ⎭ ⎩ ⎭

=

2 29 9

500 7500.70250.075 200 10 0.050 70 10

4 4116.6

Steel Cu

PL PLAE AE

P Por

or P kN

Therefore, compressive stress on steel rod

( )

σ π×= = =

×

32

2

116.6 10 N/m 26.39 MPa0.075

4

SteelSteel

PA

And compressive stress on copper rod

( )

σ π×= = =

×

32

2

116.6 10 N/m 59.38 MPa0.050

4

CuCu

PA



1.17 Thermal stress on Brass and Mild steel combination A brass rod placed within a steel tube of exactly same length. The assembly is making in such a

way that elongation of the combination will be same. To calculate the stress induced in the brass rod, steel tube when the combination is raised by toC then the following analogy have to do.

(a) Original bar before heating.

(b) Expanded position if the members are allowed to

expand freely and independently after heating.

(c) Expanded position of the compound bar i.e. final

position after heating.

• Compatibility Equation:

δ δ δ δ δ= + = −st sf Bt Bf

• Equilibrium Equation:

σ σ=s s B BA A

Assumption:

s1. L = L

2.3.

α α=

>−−

B

b s

L

Steel TensionBrass Compression

Where, δ = Expansion of the compound bar = AD in the above figure.

stδ = Free expansion of the steel tube due to temperature rise toC = s L tα

= AB in the above figure.

sfδ = Expansion of the steel tube due to internal force developed by the unequal expansion.

= BD in the above figure.

Btδ = Free expansion of the brass rod due to temperature rise toC = b L tα

= AC in the above figure.

Bfδ = Compression of the brass rod due to internal force developed by the unequal expansion.

= BD in the above figure.

And in the equilibrium equation

Tensile force in the steel tube = Compressive force in the brass rod

Where, sσ = Tensile stress developed in the steel tube.

Bσ = Compressive stress developed in the brass rod.

sA = Cross section area of the steel tube.

BA = Cross section area of the brass rod.

Let us take an example: See the Conventional Question Answer section of this chapter and the question

is “Conventional Question IES-2008” and it’s answer.



1.18 Maximum stress and elongation due to rotation

(i) 2 2

max 8Lρωσ = and ( )

2 3

12LLE

ρωδ =

(ii) 2 2

max 2Lρωσ = and ( )

2 3

3LL

Eρωδ =

For remember: You will get (ii) by multiplying by 4 of (i)

1.18 Creep When a member is subjected to a constant load over a long period of time it undergoes a slow permanent deformation and this is termed as “creep”. This is dependent on temperature. Usually at elevated temperatures creep is high.

• The materials have its own different melting point; each will creep when the homologous

temperature > 0.5. Homologous temp = Testing temperatureMelting temperature

> 0.5

A typical creep curve shows three distinct stages with different creep rates. After an initial rapid elongation εo, the creep rate decrease with time until reaching the steady state.

1) Primary creep is a period of transient creep. The creep resistance of the material increases due to material deformation.

2) Secondary creep provides a nearly constant creep rate. The average value of the creep rate during this period is called the minimum creep rate. A stage of balance between competing.

Strain hardening and recovery (softening) of the material.

3) Tertiary creep shows a rapid increase in the creep rate due to effectively reduced cross-sectional area of the specimen leading to creep rupture or failure. In this stage intergranular cracking and/or formation of voids and cavities occur.

Creep rate =c1 2cσ

Creep strain at any time = zero time strain intercept + creep rate ×Time

= 20 1

cc tσ∈ + ×

Where, 1 2, constantsc c are stressσ =

1.19 If a load P is applied suddenly to a bar then the stress & strain induced will be double than those obtained by an equal load applied gradually.

1.20 Stress produced by a load P in falling from height ’h’



21 1 σ,

being stress & strain produced by static load P & L=length of bar.

dhL

σ σ⎫⎡ ⎤⎪= + +⎢ ⎥⎬∈⎢ ⎥⎪⎣ ⎦⎭

∈

21 1A AEh

P PL⎡ ⎤

= + +⎢ ⎥⎣ ⎦

1.21 Loads shared by the materials of a compound bar made of bars x & y due to load W,

.

.

x xx

x x y y

y yy

x x y y

A EP WA E A E

A EP W

A E A E

=+

=+

1.22 Elongation of a compound bar, x x y y

PLA E A E

δ =+

1.23 Tension Test

i) True elastic limit: based on micro-strain measurement at strains on order of 2 × 10-6. Very low value and is related to the motion of a few hundred dislocations.

ii) Proportional limit: the highest stress at which stress is directly proportional to strain.

iii) Elastic limit: is the greatest stress the material can withstand without any measurable permanent strain after unloading. Elastic limit > proportional limit.

iv) Yield strength is the stress required to produce a small specific amount of

deformation. The offset yield strength can be determined by the stress

corresponding to the intersection of the stress-strain curve and a line

parallel to the elastic line offset by a strain of 0.2 or 0.1%. ( ε = 0.002 or

0.001).



• The offset yield stress is referred to proof stress either at 0.1 or 0.5% strain used for design and

specification purposes to avoid the practical difficulties of measuring the elastic limit or

proportional limit.

v) Tensile strength or ultimate tensile strength (UTS) uσ is the maximum load Pmax divided by the

original cross-sectional area Ao of the specimen.

vi) % Elongation, f o

o

L LL−

= , is chiefly influenced by uniform elongation, which is dependent on the strain-

hardening capacity of the material.

vii) Reduction of Area: o f

o

A AqA−

=

• Reduction of area is more a measure of the deformation required to produce failure and its chief

contribution results from the necking process.

• Because of the complicated state of stress state in the neck, values of reduction of area are

dependent on specimen geometry, and deformation behaviour, and they should not be taken as true material properties.

• RA is the most structure-sensitive ductility parameter and is useful in detecting quality

changes in the materials.

viii) Stress-strain response

1.24 Elastic strain and Plastic strain The strain present in the material after unloading is called the residual strain or plastic strain and the strain disappears during unloading is termed as recoverable or elastic strain. Equation of the straight line CB is given by

σ =∈ × − ∈ × =∈ ×total Plastic ElasticE E E

Carefully observe the following figures and understand which one is Elastic strain and which one is Plastic strain



Let us take an example: A 10 mm diameter tensile specimen has a 50 mm gauge length. The load corresponding to the 0.2% offset is 55 kN and the maximum load is 70 kN. Fracture occurs at 60 kN. The diameter after fracture is 8 mm and the gauge length at fracture is 65 mm. Calculate the following properties of the material from the tension test. (i) % Elongation (ii) Reduction of Area (RA) % (iii) Tensile strength or ultimate tensile strength (UTS) (iv) Yield strength (v) Fracture strength (vi) If E = 200 GPa, the elastic recoverable strain at maximum load (vii) If the elongation at maximum load (the uniform elongation) is 20%, what is the plastic strain at

maximum load?

Answer: Given, Original area ( ) ( )π −= × = ×2 2 5 20 0.010 m 7.854 10 m

4A

Area at fracture ( ) ( )π −= × = ×2 2 5 20.008 m 5.027 10 m4fA

Original gauge length (L0) = 50 mm Gauge length at fracture (L) = 65 mm Therefore

(i) % Elongation − −= × = × =0

0

65 50100% 100 30%50

L LL

(ii) Reduction of area (RA) = q − −= × = × =0

0

7.854 5.027100% 100% 36%7.854

fA AA

(iii) Tensile strength or Ultimate tensile strength (UTS), σ −

×= = =×

32

570 10 N/m 891 MPa

7.854 10max

uo

PA

(iv) Yield strength ( )σ −

×= = =×

32

555 10 N/m 700 MPa

7.854 10y

yo

PA

(v) Fracture strength ( )σ −

×= = =×

32

560 10 N/m 764MPa

7.854 10Fracture

Fo

PA

(vi) Elastic recoverable strain at maximum load ( )ε ×= = =×

6max

9/ 891 10 0.0045

200 10o

EP A

E



(vii) Plastic strain ( )ε ε ε= − = − =0.2000 0.0045 0.1955P total E

1.25 Elasticity This is the property of a material to regain its original shape

after deformation when the external forces are removed. When

the material is in elastic region the strain disappears

completely after removal of the load, The stress-strain

relationship in elastic region need not be linear and can be non-linear (example rubber). The maximum stress value below

which the strain is fully recoverable is called the elastic limit.

It is represented by point A in figure. All materials are elastic

to some extent but the degree varies, for example, both mild

steel and rubber are elastic materials but steel is more elastic

than rubber.

1.26 Plasticity When the stress in the material exceeds the elastic limit, the

material enters into plastic phase where the strain can no

longer be completely removed. Under plastic conditions

materials ideally deform without any increase in stress. A

typical stress strain diagram for an elastic-perfectly plastic

material is shown in the figure. Mises-Henky criterion gives a

good starting point for plasticity analysis.

1.27 Strain hardening If the material is reloaded from point C, it will follow the

previous unloading path and line CB becomes its new elastic

region with elastic limit defined by point B. Though the new

elastic region CB resembles that of the initial elastic region

OA, the internal structure of the material in the new state has

changed. The change in the microstructure of the material is

clear from the fact that the ductility of the material has come

down due to strain hardening. When the material is reloaded,

it follows the same path as that of a virgin material and fails

on reaching the ultimate strength which remains unaltered

due to the intermediate loading and unloading process.



1.28 Stress reversal and stress-strain hysteresis loop

We know that fatigue failure begins at a local discontinuity and when the stress at the discontinuity exceeds elastic limit there is plastic strain. The cyclic plastic strain results crack propagation and fracture.

When we plot the experimental data with reversed loading which can induce plastic stress and the true stress strain hysteresis loops is found as shown below.

True stress-strain plot with a number of stress reversals

The area of the hysteresis loop gives the energy dissipationper unit volume of the material, per stress cycle. This is termed the per unit volume damping capacity. Due to cyclic strain the elastic limit increases for annealed steel and decreases for cold drawn steel.

Here the stress range is Δσ. Δεp and Δεe are the plastic and elastic strain ranges, the total strain range being Δε. Considering that the total strain amplitude can be given as

Δε = Δεp+ Δεe



OBJECTIVE QUESTIONS (GATE, IES, IAS)

Previous 20-Years GATE Questions

Stress in a bar GATE-1. Two identical circular rods of same diameter and same length are subjected to same

magnitude of axial tensile force. One of the rods is made out of mild steel having the modulus of elasticity of 206 GPa. The other rod is made out of cast iron having the modulus of elasticity of 100 GPa. Assume both the materials to be homogeneous and isotropic and the axial force causes the same amount of uniform stress in both the rods. The stresses developed are within the proportional limit of the respective materials. Which of the following observations is correct? [GATE-2003]

(a) Both rods elongate by the same amount (b) Mild steel rod elongates more than the cast iron rod (c) Cast iron rod elongates more than the mild steel rod (d) As the stresses are equal strains are also equal in both the rods GATE-1(i).A rod of length L having uniform cross-sectional area A is subjected to a tensile force

P as shown in the figure below If the Young's modulus of the material varies linearly from E1, to E2 along the length of the rod, the normal stress developed at the section-SS is [GATE-2013]

( ) ( ) ( − )( + ) ( ) ( ) GATE-2. A steel bar of 40 mm × 40 mm square cross-section is subjected to an axial

compressive load of 200 kN. If the length of the bar is 2 m and E = 200 GPa, the elongation of the bar will be: [GATE-2006]

(a) 1.25 mm (b) 2.70 mm (c) 4.05 mm (d) 5.40 mm GATE-2(i) A bar of varying square cross-section is loaded symmetrically as shown in the figure.

Loads shown are placed on one of the axes of symmetry of cross-section. Ignoring self weight, the maximum tensile stress in 2N/ mm anywhere is [CE: GATE-2003]



100 mm

100 kN

50 mm

100 kN

50 kN (a) 16.0 (b) 20.0 (c) 25.0 (d) 30.0 GATE-2(ii) A curved member with a straight vertical leg is carrying a vertical load at Z. As shown in the

figure. The stress resultants in the XY segment are [CE: GATE-2003]

Z

Y

X

(a) bending moment, shear force and axial force (b) bending moment and axial force only (c) bending moment and shear force only (d) axial force only

True stress and true strain GATE-3. The ultimate tensile strength of a material is 400 MPa and the elongation up to

maximum load is 35%. If the material obeys power law of hardening, then the true stress-true strain relation (stress in MPa) in the plastic deformation range is: [GATE-2006]

(a) 0.30540σ ε= (b) 0.30775σ ε= (c) 0.35540σ ε= (d) 0.35775σ ε=

Elasticity and Plasticity GATE-4. An axial residual compressive stress due to a manufacturing process is present on the

outer surface of a rotating shaft subjected to bending. Under a given bending load, the fatigue life of the shaft in the presence of the residual compressive stress is:

(a) Decreased (b) Increased or decreased, depending on the external bending load[GATE-2008] (c) Neither decreased nor increased (d) Increased

GATE-5. A static load is mounted at the centre of a shaft rotating at uniform angular velocity. This shaft will be designed for [GATE-2002]

(a) The maximum compressive stress (static) (b) The maximum tensile stress (static) (c) The maximum bending moment (static) (d) Fatigue loading



GATE-6. Fatigue strength of a rod subjected to cyclic axial force is less than that of a rotating

beam of the same dimensions subjected to steady lateral force because (a) Axial stiffness is less than bending stiffness [GATE-1992] (b) Of absence of centrifugal effects in the rod (c) The number of discontinuities vulnerable to fatigue are more in the rod (d) At a particular time the rod has only one type of stress whereas the beam has both the

tensile and compressive stresses.

Relation between the Elastic Modulii GATE-7. A rod of length L and diameter D is subjected to a tensile load P. Which of the

following is sufficient to calculate the resulting change in diameter? (a) Young's modulus (b) Shear modulus [GATE-2008] (c) Poisson's ratio (d) Both Young's modulus and shear modulus GATE-8. In terms of Poisson's ratio (µ) the ratio of Young's Modulus (E) to Shear Modulus (G)

of elastic materials is [GATE-2004]

1 1( ) 2(1 ) ( ) 2(1 ) ( ) (1 ) ( ) (1 )2 2

a b c dμ μ μ μ+ − + −

GATE-9. The relationship between Young's modulus (E), Bulk modulus (K) and Poisson's ratio

(µ) is given by: [GATE-2002] (a) ( )E 3 K 1 2μ= − (b) ( )K 3 E 1 2μ= −

(c) ( )E 3 K 1 μ= − (d) ( )K 3 E 1 μ= − GATE-9(i) For an isotropic material, the relationship between the Young’s modulus (E), shear

modulus (G) and Poisson’s ratio ( )μ is given by [CE: GATE-2007]

(a) EG2(1 )

=+ μ

(b) E2(1 )

G=+ μ

(c) EG(1 )

=+ μ

(d) EG2(1 2 )

=− μ

Stresses in compound strut GATE-10. In a bolted joint two members

are connected with an axial tightening force of 2200 N. If the bolt used has metric threads of 4 mm pitch, then torque required for achieving the tightening force is

(a) 0.7Nm (b) 1.0 Nm (c) 1.4Nm (d) 2.8Nm

[GATE-2004] GATE-11. The figure below shows a steel rod of 25 mm2 cross sectional area. It is loaded at four

points, K, L, M and N. [GATE-2004, IES 1995, 1997, 1998]

Assume Esteel = 200 GPa. The total change in length of the rod due to loading is: (a) 1 µm (b) -10 µm (c) 16 µm (d) -20 µm GATE-12. A bar having a cross-sectional area of 700mm2 is subjected to axial loads at the

positions indicated. The value of stress in the segment QR is: [GATE-2006]



P Q R S (a) 40 MPa (b) 50 MPa (c) 70 MPa (d) 120 MPa GATE-12(i)A rigid bar is suspended by three rods made of the same material as shown in the

figure. The area and length of the central rod are 3A and L, respectively while that of the two outer rods are 2A and 2L, respectively. If a downward force of 50 kN is applied to the rigid bar, the forces in the central and each of the outer rods will be

(a) 16.67 kN each (b) 30 kN and 15 kN [CE: GATE-2007] (c) 30 kN and 10 kN (d) 21.4 kN and 14.3 kN

50 kN GATE-13. An ejector mechanism consists of a

helical compression spring having a spring constant of K = 981 × 103 N/m. It is pre-compressed by 100 mm from its free state. If it is used to eject a mass of 100 kg held on it, the mass will move up through a distance of

(a) 100mm (b) 500mm (c) 981 mm (d) 1000mm

[GATE-2004]

GATE-14. The figure shows a pair of pin-jointed

gripper-tongs holding an object weighing 2000 N. The co-efficient of friction (µ) at the gripping surface is 0.1 XX is the line of action of the input force and YY is the line of application of gripping force. If the pin-joint is assumed to be frictionless, then magnitude of force F required to hold the weight is:

(a) 1000 N (b) 2000 N (c) 2500 N (d) 5000 N

[GATE-2004]



GATE-15. A uniform, slender cylindrical rod is made of a homogeneous and isotropic material.

The rod rests on a frictionless surface. The rod is heated uniformly. If the radial and longitudinal thermal stresses are represented by σr and σz, respectively, then[GATE-2005]

( ) 0, 0 ( ) 0, 0 ( ) 0, 0 ( ) 0, 0r z r z r z r za b c dσ σ σ σ σ σ σ σ= = ≠ = = ≠ ≠ ≠

Thermal Effect GATE-15(i). A solid steel cube constrained on all six faces is heated so that the

temperature rises uniformly by ΔT. If the thermal coefficient of the material is α, Young’s modulus is E and the Poisson’s ratio is υ , the thermal stress developed in the cube due to heating is

( )( )

( )( )

( )( )

( )( )

2 3( ) ( ) ( ) ( )

1 2 1 2 1 2 3 1 2T E T E T E T E

a b c dα α α α

υ υ υ υΔ Δ Δ Δ

− − − −− − − −

[GATE-2012]

GATE-15(ii) A metal bar of length 100 mm is inserted between two rigid supports and its

temperature is increased by 10º C. If the coefficient of thermal expansion is 612 10 per ºC−× and the Young’s modulus is 52 10 MPa,× the stress in the bar is

(a) zero (b) 12 MPa (c) 24 Mpa (d) 2400 MPa [CE: GATE-2007]

Tensile Test GATE-16. A test specimen is stressed slightly beyond the yield point and then unloaded. Its

yield strength will [GATE-1995] (a) Decrease (b) Increase (c) Remains same (d) Becomes equal to ultimate tensile strength GATE-17. Under repeated loading a

material has the stress-strain curve shown in figure, which of the following statements is true?

(a) The smaller the shaded area, the better the material damping

(b) The larger the shaded area, the better the material damping

(c) Material damping is an independent material property and does not depend on this curve

(d) None of these

[GATE-1999]

Previous 20-Years IES Questions

Stress in a bar due to self-weight IES-1. A solid uniform metal bar of diameter D and length L is hanging vertically from its

upper end. The elongation of the bar due to self weight is: [IES-2005] (a) Proportional to L and inversely proportional to D2 (b) Proportional to L2 and inversely proportional to D2 (c) Proportional of L but independent of D (d) Proportional of U but independent of D



IES-2. The deformation of a bar under its own weight as compared to that when subjected to a direct axial load equal to its own weight will be: [IES-1998]

(a) The same (b) One-fourth (c) Half (d) Double IES-3. A rigid beam of negligible weight is supported in a horizontal position by two rods of

steel and aluminum, 2 m and 1 m long having values of cross - sectional areas 1 cm2 and 2 cm2 and E of 200 GPa and 100 GPa respectively. A load P is applied as shown in the figure [IES-2002]

If the rigid beam is to remain horizontal then (a) The forces on both sides should be equal (b) The force on aluminum rod should be twice the force on steel (c) The force on the steel rod should be twice the force on aluminum (d) The force P must be applied at the centre of the beam

Bar of uniform strength IES-4. Which one of the following statements is correct? [IES 2007] A beam is said to be of uniform strength, if (a) The bending moment is the same throughout the beam (b) The shear stress is the same throughout the beam (c) The deflection is the same throughout the beam (d) The bending stress is the same at every section along its longitudinal axis IES-5. Which one of the following statements is correct? [IES-2006] Beams of uniform strength vary in section such that (a) bending moment remains constant (b) deflection remains constant (c) maximum bending stress remains constant (d) shear force remains constant IES-6. For bolts of uniform strength, the shank diameter is made equal to [IES-2003] (a) Major diameter of threads (b) Pitch diameter of threads (c) Minor diameter of threads (d) Nominal diameter of threads IES-7. A bolt of uniform strength can be developed by [IES-1995] (a) Keeping the core diameter of threads equal to the diameter of unthreaded portion of the

bolt (b) Keeping the core diameter smaller than the diameter of the unthreaded portion (c) Keeping the nominal diameter of threads equal the diameter of unthreaded portion of the

bolt (d) One end fixed and the other end free IES-7a. In a bolt of uniform strength:

(a) Nominal diameter of thread is equal to the diameter of shank of the bolt (b) Nominal diameter of thread is larger than the diameter of shank of the bolt (c) Nominal diameter of thread is less than the diameter of shank of the bolt (d) Core diameter of threads is equal to the diameter of shank of the bolt.



[IES-2011]

Elongation of a Taper Rod IES-8. Two tapering bars of the same material are subjected to a tensile load P. The lengths

of both the bars are the same. The larger diameter of each of the bars is D. The diameter of the bar A at its smaller end is D/2 and that of the bar B is D/3. What is the ratio of elongation of the bar A to that of the bar B? [IES-2006]

(a) 3 : 2 (b) 2: 3 (c) 4 : 9 (d) 1: 3 IES-9. A bar of length L tapers uniformly from diameter 1.1 D at one end to 0.9 D at the

other end. The elongation due to axial pull is computed using mean diameter D. What is the approximate error in computed elongation? [IES-2004]

(a) 10% (b) 5% (c) 1% (d) 0.5% IES-10. The stretch in a steel rod of circular section, having a length 'l' subjected to a tensile

load' P' and tapering uniformly from a diameter d1 at one end to a diameter d2 at the other end, is given [IES-1995]

(a) 1 24

PlEd d

(b) 1 2

.plEd d

π (c)

1 2

.4

plEd d

π (d)

1 2

4 plEd dπ

IES-11. A tapering bar (diameters of end sections being d1 and d2 a bar of uniform cross-

section ’d’ have the same length and are subjected the same axial pull. Both the bars will have the same extension if’d’ is equal to [IES-1998]

( ) ( ) ( ) ( )1 2 1 2 1 21 2a b c d

2 2 2d d d d d dd d+ +

IES-11(i). A rod of length l tapers uniformly from a diameter D at one end to a diameter d at the

other. The Young’s modulus of the material is E. The extension caused by an axial load P is [IES-2012] ( ) 4( − ) ( ) 4( + ) ( ) 4 ( ) 2

Poisson’s ratio IES-12. In the case of an engineering material under unidirectional stress in the x-direction,

the Poisson's ratio is equal to (symbols have the usual meanings) [IAS 1994, IES-2000]

(a) x

y

εε

(b) x

y

σε

(c) x

y

σσ

(d) x

y

εσ

IES-13. Which one of the following is correct in respect of Poisson's ratio (v) limits for an

isotropic elastic solid? [IES-2004] (a) ν−∞ ≤ ≤∞ (b) 1/ 4 1/ 3ν≤ ≤ (c) 1 1/ 2ν− ≤ ≤ (d) 1/ 2 1/ 2ν− ≤ ≤ IES-14. Match List-I (Elastic properties of an isotropic elastic material) with List-II (Nature

of strain produced) and select the correct answer using the codes given below the Lists: [IES-1997]

List-I List-II A. Young's modulus 1. Shear strain B. Modulus of rigidity 2. Normal strain C. Bulk modulus 3. Transverse strain D. Poisson's ratio 4. Volumetric strain Codes: A B C D A B C D (a) 1 2 3 4 (b) 2 1 3 4 (c) 2 1 4 3 (d) 1 2 4 3



IES-15. If the value of Poisson's ratio is zero, then it means that [IES-1994] (a) The material is rigid. (b) The material is perfectly plastic. (c) There is no longitudinal strain in the material (d) The longitudinal strain in the material is infinite. IES-16. Which of the following is true (µ= Poisson's ratio) [IES-1992] (a) 0 1/ 2μ< < (b) 1 0μ< < (c) 1 1μ< < − (d) μ∞ < << −∞ IES-16a. If a piece of material neither expands nor contracts in volume when subjected to

stress, then the Poisson’s ratio must be (a) Zero (b) 0.25 (c) 0.33 (d) 0.5 [IES-2011]

Elasticity and Plasticity IES-17. If the area of cross-section of a wire is circular and if the radius of this circle

decreases to half its original value due to the stretch of the wire by a load, then the modulus of elasticity of the wire be: [IES-1993]

(a) One-fourth of its original value (b) Halved (c) Doubled (d) Unaffected IES-18. The relationship between the Lame’s constant ‘λ’, Young’s modulus ‘E’ and the

Poisson’s ratio ‘μ’ [IES-1997]

( ) ( )( ) ( )( ) ( ) ( ) ( )a ( ) c d 1 1 2 1 2 1 1 1

μ μ μ μλ λ λ λμ μ μ μ μ μ

= = = =+ − + − + −

E E E Eb

IES-19. Which of the following pairs are correctly matched? [IES-1994] 1. Resilience…………… Resistance to deformation. 2. Malleability …………..Shape change. 3. Creep ........................ Progressive deformation. 4. Plasticity .... ………….Permanent deformation. Select the correct answer using the codes given below: Codes: (a) 2, 3 and 4 (b) 1, 2 and 3 (c) 1, 2 and 4 (d) 1, 3 and 4 IES-19a Match List – I with List - II and select the correct answer using the code given below

the lists: [IES-2011] List –I List –II

A. Elasticity 1. Deform non-elastically without fracture B. Malleability 2. Undergo plastic deformation under tensile load C. Ductility 3. Undergo plastic deformation under compressive load D. Plasticity 4. Return to its original shape on unloading Codes A B C D A B C D (a) 1 2 3 4 (b) 4 2 3 1 (c) 1 3 2 4 (d) 4 3 2 1

IES-19b. Assertion (A): Plastic deformation is a function of applied stress, temperature and strain rate.

[IES-2010] Reason (R): Plastic deformation is accompanied by change in both the internal and external state of the material. (a) Both A and R are individually true and R is the correct explanation of A (b) Both A and R are individually true but R is NOT the correct explanation of A (c) A is true but R is false (d) A is false but R is true

Creep and fatigue IES-20. What is the phenomenon of progressive extension of the material i.e., strain

increasing with the time at a constant load, called? [IES 2007] (a) Plasticity (b) Yielding (b) Creeping (d) Breaking



IES-21. The correct sequence of creep deformation in a creep curve in order of their elongation is: [IES-2001]

(a) Steady state, transient, accelerated (b) Transient, steady state, accelerated (c) Transient, accelerated, steady state (d) Accelerated, steady state, transient IES-22. The highest stress that a material can withstand for a specified length of time

without excessive deformation is called [IES-1997] (a) Fatigue strength (b) Endurance strength (c) Creep strength (d) Creep rupture strength IES-23. Which one of the following features improves the fatigue strength of a metallic

material? [IES-2000] (a) Increasing the temperature (b) Scratching the surface (c) Overstressing (d) Under stressing IES-24. Consider the following statements: [IES-1993] For increasing the fatigue strength of welded joints it is necessary to employ 1. Grinding 2. Coating 3. Hammer peening Of the above statements (a) 1 and 2 are correct (b) 2 and 3 are correct (c) 1 and 3 are correct (d) 1, 2 and 3 are correct

Relation between the Elastic Modulii IES-25. For a linearly elastic, isotropic and homogeneous material, the number of elastic

constants required to relate stress and strain is:[IAS 1994; IES-1998, CE:GATE-2010] (a) Two (b) Three (c) Four (d) Six IES-26. E, G, K and μ represent the elastic modulus, shear modulus, bulk modulus and

Poisson's ratio respectively of a linearly elastic, isotropic and homogeneous material. To express the stress-strain relations completely for this material, at least[IES-2006]

(a) E, G and μ must be known (b) E, K and μ must be known (c) Any two of the four must be known (d) All the four must be known IES-27. The number of elastic constants for a completely anisotropic elastic material which

follows Hooke's law is: [IES-1999] (a) 3 (b) 4 (c) 21 (d) 25 IES-28. What are the materials which show direction dependent properties, called? (a) Homogeneous materials (b) Viscoelastic materials[IES 2007, IES-2011] (c) Isotropic materials (d) Anisotropic materials IES-29. An orthotropic material, under plane stress condition will have: [IES-2006] (a) 15 independent elastic constants (b) 4 independent elastic constants (c) 5 independent elastic constants (d) 9 independent elastic constants IES-30. Match List-I (Properties) with List-II (Units) and select the correct answer using the

codes given below the lists: [IES-2001] List I List II A. Dynamic viscosity 1. Pa B. Kinematic viscosity 2. m2/s C. Torsional stiffness 3. Ns/m2

D. Modulus of rigidity 4. N/m Codes: A B C D A B C D (a) 3 2 4 1 (b) 5 2 4 3 (b) 3 4 2 3 (d) 5 4 2 1 IES-31. Young's modulus of elasticity and Poisson's ratio of a material are 1.25 × 105 MPa and

0.34 respectively. The modulus of rigidity of the material is: [IAS 1994, IES-1995, 2001, 2002, 2007]



(a) 0.4025 ×105 Mpa (b) 0.4664 × 105 Mpa (c) 0.8375 × 105 MPa (d) 0.9469 × 105 MPa IES-31(i). Consider the following statements: Modulus of rigidity and bulk modulus of a material are found to be 60 GPa and 140

GPa respectively. Then [IES-2013] 1. Elasticity modulus is nearly 200 GPa 2. Poisson’s ratio is nearly 0.3 3. Elasticity modulus is nearly 158 GPa 4. Poisson’s ratio is nearly 0.25 Which of these statements are correct? (a) 1 and 3 (b) 2 and 4 (c) 1 and 4 (d) 2 and 3 IES-32. In a homogenous, isotropic elastic material, the modulus of elasticity E in terms of G

and K is equal to [IAS-1995, IES - 1992]

(a)3

9G K

KG+

(b) 39G K

KG+

(c) 9

3KG

G K+ (d)

93

KGK G+

IES-33. What is the relationship between the linear elastic properties Young's modulus (E),

rigidity modulus (G) and bulk modulus (K)? [IES-2008]

1 9 3 3 9 1 9 3 1 9 1 3(a) (b) (c) (d)E K G E K G E K G E K G

= + = + = + = +

IES-34. What is the relationship between the liner elastic properties Young’s modulus (E),

rigidity modulus (G) and bulk modulus (K)? [IES-2009]

(a) 9

KGEK G

=+

(b) 9KGEK G

=+

(c) 9

3KGE

K G=

+ (d)

93

KGEK G

=+

IES-35. If E, G and K denote Young's modulus, Modulus of rigidity and Bulk Modulus,

respectively, for an elastic material, then which one of the following can be possibly true? [IES-2005]

(a) G = 2K (b) G = E (c) K = E (d) G = K = E IES-36. If a material had a modulus of elasticity of 2.1 × 106 kgf/cm2 and a modulus of rigidity

of 0.8 × 106 kgf/cm2 then the approximate value of the Poisson's ratio of the material would be: [IES-1993]

(a) 0.26 (b) 0.31 (c) 0.47 (d) 0.5 IES-37. The modulus of elasticity for a material is 200 GN/m2 and Poisson's ratio is 0.25. What is the modulus of rigidity? [IES-2004] (a) 80 GN/m2 (b) 125 GN/m2 (c) 250 GN/m2 (d) 320 GN/m2

IES-38. Consider the following statements: [IES-2009] 1. Two-dimensional stresses applied to a thin plate in its own plane represent the

plane stress condition. 2. Under plane stress condition, the strain in the direction perpendicular to the

plane is zero. 3. Normal and shear stresses may occur simultaneously on a plane. Which of the above statements is /are correct? (a) 1 only (b) 1 and 2 (c) 2 and 3 (d) 1 and 3 IES-38(i). A 16 mm diameter bar elongates by 0.04% under a tensile force of 16 kN. The average

decrease in diameter is found to be 0.01% Then: [IES-2013] 1. E = 210 GPa and G = 77 GPa 2. E = 199 GPa and v = 0.25 3. E = 199 GPa and v = 0.30 4. E = 199 GPa and G = 80 GPa Which of these values are correct?



(a) 3 and 4 (b) 2 and 4 (c) 1 and 3 (d) 1 and 4

Stresses in compound strut IES-39. Eight bolts are to be selected for fixing the cover plate of a cylinder subjected to a

maximum load of 980·175 kN. If the design stress for the bolt material is 315 N/mm2, what is the diameter of each bolt? [IES-2008]

(a) 10 mm (b) 22 mm (c) 30 mm (d) 36 mm IES-40. For a composite consisting of a bar enclosed inside a tube of another material when

compressed under a load 'w' as a whole through rigid collars at the end of the bar. The equation of compatibility is given by (suffixes 1 and 2) refer to bar and tube respectively [IES-1998]

1 2 1 21 2 1 2

1 1 2 2 1 2 2 1

( ) ( ) . ( ) ( )W W W Wa W W W b W W Const c dA E A E A E A E

+ = + = = =

IES-41. When a composite unit consisting of a steel rod surrounded by a cast iron tube is subjected to an axial load. [IES-2000]

Assertion (A): The ratio of normal stresses induced in both the materials is equal to the ratio of Young's moduli of respective materials.

Reason (R): The composite unit of these two materials is firmly fastened together at the ends to ensure equal deformation in both the materials.

(a) Both A and R are individually true and R is the correct explanation of A (b) Both A and R are individually true but R is not the correct explanation of A (c) A is true but R is false (d) A is false but R is true IES-42. The figure below shows a steel rod of 25 mm2 cross sectional area. It is loaded at four

points, K, L, M and N. [GATE-2004, IES 1995, 1997, 1998]

Assume Esteel = 200 GPa. The total change in length of the rod due to loading is (a) 1 µm (b) -10 µm (c) 16 µm (d) -20 µm IES-43. The reactions at the rigid

supports at A and B for the bar loaded as shown in the figure are respectively.

(a) 20/3 kN,10/3 kN (b) 10/3 kN, 20/3 kN (c) 5 kN, 5 kN (d) 6 kN, 4 kN

[IES-2002, IES-2011; IAS-2003] IES-43(i) In the arrangement as shown in the figure, the stepped steel bar ABC is loaded by a

load P. The material has Young’s modulus E = 200 GPa and the two portions. AB and BC have area of cross section 2 21 cm and 2cm respectively. The magnitude of load P required to fill up the gap of 0.75 mm is: [IES-2013]



Gap 0.75 mm 1 m 1 m

B P C A

(a) 10 kN (b) 15 kN (c) 20 kN (d) 25 kN IES-44. Which one of the following is correct? [IES-2008] When a nut is tightened by placing a washer below it, the bolt will be subjected to (a) Compression only (b) Tension (c) Shear only (d) Compression and shear IES-45. Which of the following stresses are associated with the tightening of nut on a bolt?

[IES-1998] 1. Tensile stress due to the stretching of bolt 2. Bending stress due to the bending of bolt 3. Crushing and shear stresses in threads 4. Torsional shear stress due to frictional resistance between the nut and the bolt. Select the correct answer using the codes given below Codes: (a) 1, 2 and 4 (b) 1, 2 and 3 (c) 2, 3 and 4 (d) 1, 3 and 4

Thermal effect IES-46. A 100 mm × 5 mm × 5 mm steel bar free to expand is heated from 15°C to 40°C. What

shall be developed? [IES-2008] (a) Tensile stress (b) Compressive stress (c) Shear stress (d) No stress IES-47. Which one of the following statements is correct? [GATE-1995; IES 2007, 2011] If a material expands freely due to heating, it will develop (a) Thermal stress (b) Tensile stress (c) Compressive stress (d) No stress IES-48. A cube having each side of length a, is constrained in all directions and is heated

uniformly so that the temperature is raised to T°C. If α is the thermal coefficient of expansion of the cube material and E the modulus of elasticity, the stress developed in the cube is: [IES-2003]

(a) TEαγ

(b) ( )1 2TEα

γ− (c)

2TEαγ

(d) ( )1 2TEα

γ+

IES-49. Consider the following statements: [IES-2002] Thermal stress is induced in a component in general, when

1. A temperature gradient exists in the component 2. The component is free from any restraint 3. It is restrained to expand or contract freely

Which of the above statements are correct? (a) 1 and 2 (b) 2 and 3 (c) 3 alone (d) 2 alone IES-49(i). In a body, thermal stress is induced because of the existence of: [IES-2013] (a) Latent heat (b) Total heat (c) Temperature gradient (d) Specific heat IES-50. A steel rod 10 mm in diameter and 1m long is heated from 20°C to 120°C, E = 200 GPa

and α = 12 × 10-6 per °C. If the rod is not free to expand, the thermal stress developed is: [IAS-2003, IES-1997, 2000, 2006]



(a) 120 MPa (tensile) (b) 240 MPa (tensile) (c) 120 MPa (compressive) (d) 240 MPa (compressive) IES-51. A cube with a side length of 1 cm is heated uniformly 1° C above the room

temperature and all the sides are free to expand. What will be the increase in volume of the cube? (Given coefficient of thermal expansion is α per °C)

(a) 3 α cm3 (b) 2 α cm3 (c) α cm3 (d) zero [IES-2004] IES-52. A bar of copper and steel form a composite system. [IES-2004, 2012] They are heated to a temperature of 40 ° C. What type of stress is induced in the

copper bar? (a) Tensile (b) Compressive (c) Both tensile and compressive (d) Shear IES-53. -6 oα=12.5×10 / C, E = 200GPa If the rod fitted strongly between the supports as shown

in the figure, is heated, the stress induced in it due to 20oC rise in temperature will be: [IES-1999]

(a) 0.07945 MPa (b) -0.07945 MPa (c) -0.03972 MPa (d) 0.03972 MPa

IES-54. The temperature stress is a function of [IES-1992] 1. Coefficient of linear expansion 2. Temperature rise 3. Modulus of elasticity The correct answer is: (a) 1 and 2 only (b) 1 and 3 only (c) 2 and 3 only (d) 1, 2 and 3

Impact loading IES-55. Assertion (A): Ductile materials generally absorb more impact loading than a brittle

material [IES-2004] Reason (R): Ductile materials generally have higher ultimate strength than brittle

materials (a) Both A and R are individually true and R is the correct explanation of A (b) Both A and R are individually true but R is not the correct explanation of A (c) A is true but R is false (d) A is false but R is true IES-56. Assertion (A): Specimens for impact testing are never notched. [IES-1999] Reason (R): A notch introduces tri-axial tensile stresses which cause brittle fracture. (a) Both A and R are individually true and R is the correct explanation of A (b) Both A and R are individually true but R is NOT the correct explanation of A (c) A is true but R is false (d) A is false but R is true

Tensile Test IES-57. During tensile-testing of a specimen using a Universal Testing Machine, the

parameters actually measured include [IES-1996] (a) True stress and true strain (b) Poisson’s ratio and Young's modulus (c) Engineering stress and engineering strain (d) Load and elongation



IES-58. In a tensile test, near the elastic limit zone [IES-2006] (a) Tensile stress increases at a faster rate (b) Tensile stress decreases at a faster rate (c) Tensile stress increases in linear proportion to the stress (d) Tensile stress decreases in linear proportion to the stress IES-59. Match List-I (Types of Tests and Materials) with List-II (Types of Fractures) and

select the correct answer using the codes given below the lists: List I List-II [IES-2002; IAS-2004] (Types of Tests and Materials) (Types of Fractures) A. Tensile test on CI 1. Plain fracture on a transverse plane B. Torsion test on MS 2. Granular helecoidal fracture C. Tensile test on MS 3. Plain granular at 45° to the axis D. Torsion test on CI 4. Cup and Cone 5. Granular fracture on a transverse plane Codes: A B C D A B C D (a) 4 2 3 1 (c) 4 1 3 2 (b) 5 1 4 2 (d) 5 2 4 1 IES-60. Which of the following materials generally exhibits a yield point? [IES-2003] (a) Cast iron (b) Annealed and hot-rolled mild steel (c) Soft brass (d) Cold-rolled steel IES-61. For most brittle materials, the ultimate strength in compression is much large then

the ultimate strength in tension. The is mainly due to [IES-1992] (a) Presence of flaws and microscopic cracks or cavities (b) Necking in tension (c) Severity of tensile stress as compared to compressive stress (d) Non-linearity of stress-strain diagram IES-61(i). A copper rod 400 mm long is pulled in tension to a length of 401.2 mm by applying a

tensile load of 330 MPa. If the deformation is entirely elastic, the Young’s modulus of copper is [IES-2012] (a) 110 GPA (b) 110 MPa (c) 11 GPa (d) 11 MPa

IES-62. What is the safe static tensile load for a M36 × 4C bolt of mild steel having yield stress

of 280 MPa and a factor of safety 1.5? [IES-2005] (a) 285 kN (b) 190 kN (c) 142.5 kN (d) 95 kN IES-63. Which one of the following properties is more sensitive to increase in strain rate?

[IES-2000] (a) Yield strength (b) Proportional limit (c) Elastic limit (d) Tensile strength IES-64. A steel hub of 100 mm internal diameter and uniform thickness of 10 mm was heated

to a temperature of 300oC to shrink-fit it on a shaft. On cooling, a crack developed parallel to the direction of the length of the hub. Consider the following factors in this regard: [IES-1994]

1. Tensile hoop stress 2. Tensile radial stress 3. Compressive hoop stress 4. Compressive radial stress The cause of failure is attributable to (a) 1 alone (b) 1 and 3 (c) 1, 2 and 4 (d) 2, 3 and 4 IES-65. If failure in shear along 45° planes is to be avoided, then a material subjected to

uniaxial tension should have its shear strength equal to at least [IES-1994] (a) Tensile strength (b) Compressive strength (c) Half the difference between the tensile and compressive strengths. (d) Half the tensile strength.



IES-66. Select the proper sequence [IES-1992] 1. Proportional Limit 2. Elastic limit 3. Yielding 4. Failure (a) 2, 3, 1, 4 (b) 2, 1, 3, 4 (c) 1, 3, 2, 4 (d) 1, 2, 3, 4 IES-67. Elastic limit of cast iron as compared to its ultimate breaking strength is

(a) Half (b) Double [IES-2012] (c) Approximately (d) None of the above

IES-68. Statement (I): Steel reinforcing bars are used in reinforced cement concrete.

Statement (II): Concrete is weak in compression. [IES-2012] (a) Both Statement (I) and Statement (II) are individually true and Statement (II) is the correct explanation of Statement (I)

(b) Both Statement (I) and Statement (II) are individually true but Statement (II) is not the correct explanation of Statement (I) (c) Statement (I) is true but Statement (II) is false (d) Statement (I) is false but Statement (II) is true

Previous 20-Years IAS Questions

Stress in a bar due to self-weight IAS-1. A heavy uniform rod of length 'L' and material density 'δ' is hung vertically with its

top end rigidly fixed. How is the total elongation of the bar under its own weight expressed? [IAS-2007]

(a) 22 L g

Eδ

(b) 2L g

Eδ

(c) 2

2L g

Eδ

(d) 2

2L gE

δ

IAS-2. A rod of length 'l' and cross-section area ‘A’ rotates about an axis passing through one

end of the rod. The extension produced in the rod due to centrifugal forces is (w is the weight of the rod per unit length and ω is the angular velocity of rotation of the rod). [IAS 1994]

(a) gEwl 2ω

(b) gEwl

3

32ω (c)

gEwl32ω

(d) 323

wlgE

ω

Elongation of a Taper Rod IAS-3. A rod of length, "ι " tapers uniformly from a diameter ''D1' to a diameter ''D2' and

carries an axial tensile load of "P". The extension of the rod is (E represents the modulus of elasticity of the material of the rod) [IAS-1996]

(a) 1 2

4 1π

PED D

1 2

4 1( )π

PEbD D

(c)1 2

14

EPD D

π (d) 1 2

14

PED Dπ

Poisson’s ratio IAS-4. In the case of an engineering material under unidirectional stress in the x-direction,

the Poisson's ratio is equal to (symbols have the usual meanings) [IAS 1994, IES-2000]

(a) x

y

εε

(b) x

y

σε

(c) x

y

σσ

(d) x

y

εσ

IAS-5. Assertion (A): Poisson's ratio of a material is a measure of its ductility. Reason (R): For every linear strain in the direction of force, Poisson's ratio of the

material gives the lateral strain in directions perpendicular to the direction of force. [IAS-1999]



(a) Both A and R are individually true and R is the correct explanation of A (b) Both A and R are individually true but R is not the correct explanation of A (c) A is true but R is false (d) A is false but R is true IAS-6. Assertion (A): Poisson's ratio is a measure of the lateral strain in all direction

perpendicular to and in terms of the linear strain. [IAS-1997] Reason (R): The nature of lateral strain in a uni-axially loaded bar is opposite to that

of the linear strain. (a) Both A and R are individually true and R is the correct explanation of A (b) Both A and R are individually true but R is not the correct explanation of A (c) A is true but R is false (d) A is false but R is true

Elasticity and Plasticity IAS-7. A weight falls on a plunger fitted in a container filled with oil thereby producing a

pressure of 1.5 N/mm2 in the oil. The Bulk Modulus of oil is 2800 N/mm2. Given this situation, the volumetric compressive strain produced in the oil will be:[IAS-1997]

(a) 400 × 10-6 (b) 800 × 106 (c) 268 × 106 (d) 535 × 10-6

Relation between the Elastic Modulii IAS-8. For a linearly elastic, isotropic and homogeneous material, the number of elastic

constants required to relate stress and strain is: [IAS 1994; IES-1998] (a) Two (b) Three (c) Four (d) Six IAS-9. The independent elastic constants for a homogenous and isotropic material are (a) E, G, K, v (b) E, G, K (c) E, G, v (d) E, G [IAS-1995] IAS-10. The unit of elastic modulus is the same as those of [IAS 1994] (a) Stress, shear modulus and pressure (b) Strain, shear modulus and force (c) Shear modulus, stress and force (d) Stress, strain and pressure. IAS-11. Young's modulus of elasticity and Poisson's ratio of a material are 1.25 × 105 MPa and

0.34 respectively. The modulus of rigidity of the material is: [IAS 1994, IES-1995, 2001, 2002, 2007] (a) 0.4025 × 105 MPa (b) 0.4664 × 105 MPa (c) 0.8375 × 105 MPa (d) 0.9469 × 105 MPa IAS-12. The Young's modulus of elasticity of a material is 2.5 times its modulus of rigidity.

The Posson's ratio for the material will be: [IAS-1997] (a) 0.25 (b) 0.33 (c) 0.50 (d) 0.75 IAS-13. In a homogenous, isotropic elastic material, the modulus of elasticity E in terms of G

and K is equal to [IAS-1995, IES - 1992]

(a)3

9G K

KG+

(b) 39G K

KG+

(c) 9

3KG

G K+ (d)

93

KGK G+

IAS-14. The Elastic Constants E and K are related as ( μ is the Poisson’s ratio) [IAS-1996] (a) E = 2k (1 – 2 μ ) (b) E = 3k (1- 2 μ ) (c) E = 3k (1 + μ ) (d) E = 2K(1 + 2 μ ) IAS-15. For an isotropic, homogeneous and linearly elastic material, which obeys Hooke's

law, the number of independent elastic constant is: [IAS-2000] (a) 1 (b) 2 (c) 3 (d) 6 IAS-16. The moduli of elasticity and rigidity of a material are 200 GPa and 80 GPa,

respectively. What is the value of the Poisson's ratio of the material? [IAS-2007] (a) 0·30 (b) 0·26 (c) 0·25 (d) 0·24



Stresses in compound strut IAS-17. The reactions at the rigid supports at A and B for the bar loaded as shown in the

figure are respectively. [IES-2002; IAS-2003] (a) 20/3 kN,10/3 Kn (b) 10/3 kN, 20/3 kN (c) 5 kN, 5 kN (d) 6 kN, 4 kN

Thermal effect IAS-18. A steel rod 10 mm in diameter and 1m long is heated from 20°C to 120°C, E = 200 GPa

and α = 12 × 10-6 per °C. If the rod is not free to expand, the thermal stress developed is: [IAS-2003, IES-1997, 2000, 2006]

(a) 120 MPa (tensile) (b) 240 MPa (tensile) (c) 120 MPa (compressive) (d) 240 MPa (compressive) IAS-19. A. steel rod of diameter 1 cm and 1 m long is heated from 20°C to 120°C. Its

612 10 / Kα −= × and E=200 GN/m2. If the rod is free to expand, the thermal stress developed in it is: [IAS-2002]

(a) 12 × 104 N/m2 (b) 240 kN/m2 (c) zero (d) infinity IAS-20. Which one of the following pairs is NOT correctly matched? [IAS-1999] (E = Young's modulus, α = Coefficient of linear expansion, T = Temperature rise, A =

Area of cross-section, l= Original length) (a) Temperature strain with permitted expansion δ ….. ( Tlα δ− ) (b) Temperature stress ….. TEα (c) Temperature thrust ….. TEAα

(d) Temperature stress with permitted expansion ….. ( )E Tl

lα δ−

Impact loading IAS-21. Match List I with List II and select the correct answer using the codes given below

the lists: [IAS-1995] List I (Property) List II (Testing Machine) A. Tensile strength 1. Rotating Bending Machine B. Impact strength 2. Three-Point Loading Machine C. Bending strength 3. Universal Testing Machine D. Fatigue strength 4. Izod Testing Machine Codes: A B C D A B C D (a) 4 3 2 1 (b) 3 2 1 4 (c) 2 1 4 3 (d) 3 4 2 1

Tensile Test IAS-22. A mild steel specimen is tested in tension up to fracture in a Universal Testing

Machine. Which of the following mechanical properties of the material can be evaluated from such a test? [IAS-2007]

1. Modulus of elasticity 2. Yield stress 3. Ductility 4. Tensile strength 5. Modulus of rigidity Select the correct answer using the code given below: (a) 1, 3, 5 and 6 (b) 2, 3, 4 and 6 (c) 1, 2, 5 and 6 (d) 1, 2, 3 and 4



IAS-23. In a simple tension test, Hooke's law is valid upto the [IAS-1998] (a) Elastic limit (b) Limit of proportionality (c) Ultimate stress (d) Breaking point IAS-24. Lueder' lines on steel specimen under simple tension test is a direct indication of

yielding of material due to slip along the plane [IAS-1997] (a) Of maximum principal stress (b) Off maximum shear (c) Of loading (d) Perpendicular to the direction of loading IAS-25. The percentage elongation of a material as obtained from static tension test depends

upon the [IAS-1998] (a) Diameter of the test specimen (b) Gauge length of the specimen (c) Nature of end-grips of the testing machine (d) Geometry of the test specimen IAS-26. Match List-I (Types of Tests and Materials) with List-II (Types of Fractures) and

select the correct answer using the codes given below the lists: List I List-II [IES-2002; IAS-2004] (Types of Tests and Materials) (Types of Fractures) A. Tensile test on CI 1. Plain fracture on a transverse plane B. Torsion test on MS 2. Granular helecoidal fracture C. Tensile test on MS 3. Plain granular at 45° to the axis D. Torsion test on CI 4. Cup and Cone 5. Granular fracture on a transverse plane Codes: A B C D A B C D (a) 4 2 3 1 (c) 4 1 3 2 (b) 5 1 4 2 (d) 5 2 4 1 IAS-27. Assertion (A): For a ductile material stress-strain curve is a straight line up to the

yield point. [IAS-2003] Reason (R): The material follows Hooke's law up to the point of proportionality. (a) Both A and R are individually true and R is the correct explanation of A (b) Both A and R are individually true but R is not the correct explanation of A (c) A is true but R is false (d) A is false but R is true IAS-28. Assertion (A): Stress-strain curves for brittle material do not exhibit yield point.

[IAS-1996] Reason (R): Brittle materials fail without yielding. (a) Both A and R are individually true and R is the correct explanation of A (b) Both A and R are individually true but R is NOT the correct explanation of A (c) A is true but R is false (d) A is false but R is true IAS-29. Match List I (Materials) with List II (Stress-Strain curves) and select the correct

answer using the codes given below the Lists: [IAS-2001]



Codes: A B C D A B C D (a) 3 1 4 1 (b) 3 2 4 2 (c) 2 4 3 1 (d) 4 1 3 2 IAS-30. The stress-strain curve of an ideal elastic strain hardening material will be as

[IAS-1998]

IAS-31. An idealised stress-strain curve for a perfectly plastic material is given by

[IAS-1996]

IAS-32. Match List I with List II and select the correct answer using the codes given below

the Lists: [IAS-2002] List I List II A. Ultimate strength 1. Internal structure B. Natural strain 2. Change of length per unit instantaneous length C. Conventional strain 3. Change of length per unit gauge length D. Stress 4. Load per unit area Codes: A B C D A B C D (a) 1 2 3 4 (b) 4 3 2 1 (c) 1 3 2 4 (d) 4 2 3 1 IAS-33. What is the cause of failure of a short MS strut under an axial load? [IAS-2007] (a) Fracture stress (b) Shear stress (c) Buckling (d) Yielding IAS-34. Match List I with List II and select the correct answer using the codes given the lists:

[IAS-1995] List I List II A. Rigid-Perfectly plastic

B. Elastic-Perfectly plastic

C. Rigid-Strain hardening



D. Linearly elastic

Codes: A B C D A B C D (a) 3 1 4 2 (b) 1 3 2 4 (c) 3 1 2 4 (d) 1 3 4 2 IAS-35. Which one of the following materials is highly elastic? [IAS-1995] (a) Rubber (b) Brass (c) Steel (d) Glass IAS-36. Assertion (A): Hooke's law is the constitutive law for a linear elastic material. Reason (R) Formulation of the theory of elasticity requires the hypothesis that there

exists a unique unstressed state of the body, to which the body returns whenever all the forces are removed. [IAS-2002]

(a) Both A and R are individually true and R is the correct explanation of A (b) Both A and R are individually true but R is not the correct explanation of A (c) A is true but R is false (d) A is false but R is true IAS-37. Consider the following statements: [IAS-2002] 1. There are only two independent elastic constants. 2. Elastic constants are different in orthogonal directions. 3. Material properties are same everywhere. 4. Elastic constants are same in all loading directions. 5. The material has ability to withstand shock loading. Which of the above statements are true for a linearly elastic, homogeneous and

isotropic material? (a) 1, 3, 4 and 5 (b) 2, 3 and 4 (c) 1, 3 and 4 (d) 2 and 5 IAS-38. Which one of the following pairs is NOT correctly matched? [IAS-1999] (a) Uniformly distributed stress …. Force passed through the centroid of the cross-section (b) Elastic deformation …. Work done by external forces during deformation is dissipated fully as heat (c) Potential energy of strain …. Body is in a state of elastic deformation (d) Hooke's law …. Relation between stress and strain IAS-39. A tensile bar is stressed to 250 N/mm2 which is beyond its elastic limit. At this stage

the strain produced in the bar is observed to be 0.0014. If the modulus of elasticity of the material of the bar is 205000 N/mm2 then the elastic component of the strain is very close to [IAS-1997]

(a) 0.0004 (b) 0.0002 (c) 0.0001 (d) 0.00005

OBJECTIVE ANSWERS

GATE-1. Ans. (c) PL 1L or L [AsP, L and A is same]AE E

δ δ= ∞

( )( ) ( ) ( )mild steel CI

CI MSMSC.I

L E 100 L LL E 206

δδ δ

δ= = ∴ >

GATE-1(i) Ans. (a)

GATE-2. Ans. (a) ( )( ) 9

200 1000 2PLL m 1.25mmAE 0.04 0.04 200 10

δ× ×

= = =× × ×

GATE-2(i) Ans. (c)



The stress in lower bar = 250 ×1000 = 20 N/ mm50 × 50

The stress in upper bar = 2250 ×1000 = 25 N/ mm100 ×100

Thus the maximum tensile anywhere in the bar is 225 N/ mm GATE-2(ii) Ans. (d) There is no eceentricity between the XY segment and the load. So, it is subjected to axial force

only. But the curved YZ segment is subjected to axial force, shear force and bending moment. GATE-3. Ans. (b) A true stress – true strain curve in

tension nkσ ε= k = Strength co-efficient = 400 ×

(1.35) = 540 MPa n = Strain – hardening exponent =

0.35

GATE-4. Ans. (d)

A cantilever-loaded rotating beam, showing the normal distribution of surface stresses. (i.e.,

tension at the top and compression at the bottom)

The residual compressive stresses induced.

Net stress pattern obtained when loading a surface treated beam. The reduced magnitude of the tensile stresses contributes to increased fatigue life.

GATE-5. Ans. (d) GATE-6. Ans. (d) GATE-7. Ans. (d) For longitudinal strain we need Young's modulus and for calculating transverse strain

we need Poisson's ratio. We may calculate Poisson's ratio from )1(2 μ+= GE for that we need Shear modulus.

GATE-8. Ans. (a)

GATE-9. Ans. (a) ( ) ( ) 9KGRemember E 2G 1 3K 1 23K G

μ μ= + = − =+

GATE-9(i) Ans.(a)


hp

Cross-Out

hp

Cross-Out

hp

Cross-Out


GATE-10. Ans. (c) 0.004T F r 2200 Nm 1.4Nm2π

= × = × =

GATE-11. Ans. (b) First draw FBD of all parts separately then

Total change in length = PLAE∑

GATE-12. Ans. (a)

F.B.D

QRP 28000 MPa 40MPaA 700

σ = = =

GATE-12(i) Ans. (c) If the force in each of outer rods is 0P and force in the central rod is P ,c then + =02P P 50c …(i) Also, the elongation of central rod and outer rods is same.

∴ =0 0 C C

0 C

P L P LA E A E

⇒ × ×=0 CP 2L P L

2 A 3 A

⇒ =C 0P 3P …(ii) Solving (i) and (ii) we get = =C 0P 30kN and P 10kN GATE-13. Ans. (a) No calculation needed it is pre-compressed by 100 mm from its free state. So it can’t

move more than 100 mm. choice (b), (c) and (d) out. GATE-14. Ans. (d) Frictional force required = 2000 N

Force needed to produce 2000N frictional force at Y-Y section = 2000 20000N0.1

=

So for each side we need (Fy) = 10000 N force Taking moment about PIN

y

y

F 50 10000 50F 50 F 100 or F 5000N100 100× ×× = × = = =

GATE-15. Ans. (a) Thermal stress will develop only when you prevent the material to contrast/elongate.

As here it is free no thermal stress will develop. GATE-15(i). Ans. (a) ( )33 3

3

1a T aV pV K a

α+ −Δ= =

( )

3

3 1 2

pOr TE

α

υ

=

− ( )

( )( )

( )( ) . .

1 2 1 2T E T E

Or p or stress p i e compressiveα α

συ υ

Δ Δ= = − = −

− −

Same question was asked in IES-2003 please refer question no. IES-48 in this chapter. GATE-15(ii). Ans. (c) Temperature stress = −α = × × × × =6 5TE 12 10 10 2 10 24 MPa GATE-16. Ans. (b)



GATE-17. Ans. (b)

IES

IES-1. Ans. (d) π ρ

δ δπ

× × × ×= = ∞

× ×

2

22

D L g LWL 4 or L2AE D2 E

4

IES-2. Ans. (c) IES-3. Ans. (b) IES-4. Ans. (d) IES-5. Ans. (c) IES-6. Ans. (c) IES-7. Ans. (a) IES-7a. Ans. (d)

IES-8. Ans. (b) Elongation of a taper rod ( )1 2

PLld d E

4

δπ

=

( )( )

( )( )

2A B

2B A

l d D / 3 2orl d D / 2 3

δδ

⎛ ⎞= = =⎜ ⎟⎝ ⎠

IES-9. Ans. (c) ( )act

1 2

PL PLActual elongation of the bar ld d E 1.1D 0.9D E

4 4

δπ π

= =⎛ ⎞ ⎛ ⎞× ×⎜ ⎟ ⎜ ⎟⎝ ⎠ ⎝ ⎠

( )

( ) ( ) ( )( )

=×

− ⎛ ⎞∴ = × = − × =⎜ ⎟×⎝ ⎠

2Cal

2act cal

cal

PLCalculated elongation of the bar lD E4

l l DError % 100 1 100% 1%l 1.1D 0.9D

δπ

δ δδ

IES-10. Ans. (d) ( )act

1 2

PLActual elongation of the bar ld d E

4

δπ

=⎛ ⎞⎜ ⎟⎝ ⎠

IES-11. Ans. (b) IES-11(i). Ans. (c) IES-12. Ans. (a) IES-13. Ans. (c) Theoretically 1 1/ 2 but practically 0 1/ 2μ μ− < < < < IES-14. Ans. (c) IES-15. Ans. (a) If Poisson's ratio is zero, then material is rigid. IES-16. Ans. (a) IES-16a. Ans. (d) IES-17. Ans. (d) Note: Modulus of elasticity is the property of material. It will remain same. IES-18. Ans. (a) IES-19. Ans. (a) Strain energy stored by a body within elastic limit is known as resilience.



IES-19b. Ans. (b) Plastic deformation • Following the elastic deformation, material undergoes plastic deformation. • Also characterized by relation between stress and strain at constant strain rate and temperature. • Microscopically…it involves breaking atomic bonds, moving atoms, then restoration of bonds. • Stress-Strain relation here is complex because of atomic plane movement, dislocation movement,

and the obstacles they encounter. • Crystalline solids deform by processes – slip and twinning in particular directions. • Amorphous solids deform by viscous flow mechanism without any directionality. • Equations relating stress and strain are called constitutive equations. • A true stress-strain curve is called flow curve as it gives the stress required to cause the material to

flow plastically to certain strain. IES-20. Ans. (c) IES-21. Ans. (b) IES-22. Ans. (c) IES-23. Ans. (d) IES-24. Ans. (c) A polished surface by grinding can take more number of cycles than a part with rough

surface. In Hammer peening residual compressive stress lower the peak tensile stress IES-25. Ans. (a) IES-26. Ans. (c) IES-27. Ans. (c) IES-28. Ans. (d) IES-29. Ans. (d) IES-30. Ans. (a) IES-31. Ans.(b) )1(2 μ+= GE or 1.25x105 = 2G(1+0.34) or G = 0.4664 × 105 MPa IES-31(i). Ans. (d) IES-32. Ans. (c)

IES-33. Ans. (d) ( ) ( ) 9KGE 2G 1 3K 1 23K G

μ μ= + = − =+

IES-34. Ans. (d) ( ) ( ) 9KGE 2G 1 3K 1 23K G

μ μ= + = − =+

IES-35. Ans.(c) ( ) ( ) 9KGE 2G 1 3K 1 23K G

μ μ= + = − =+

1the value of must be between 0 to 0.5 so E never equal to G but if then3

E k so ans. is c

μ μ =

=

IES-36. Ans. (b) Use ( )2 1E G μ= +

IES-37. Ans. (a) ( ) ( ) ( )2E 200E 2G 1 or G 80GN / m

2 1 2 1 0.25μ

μ= + = = =

+ × +

IES-38. Ans. (d) Under plane stress condition, the strain in the direction perpendicular to the plane is not zero. It has been found experimentally that when a body is stressed within elastic limit, the lateral strain bears a constant ratio to the linear strain. [IES-2009]

IES-38(i). Ans. (b)

IES-39. Ans. (b) ( )2d P 980175Total load P 8 or d 22.25mm

4 2 2 315πσ

πσ π= × × = = =

×

IES-40. Ans. (c) Compatibility equation insists that the change in length of the bar must be compatible with the boundary conditions. Here (a) is also correct but it is equilibrium equation.

IES-41. Ans. (a) IES-42. Ans. (b) First draw FBD of all parts separately then

Total change in length = PLAE∑

IES-43. Ans. (a) Elongation in AC = length reduction in CB

A BR 1 R 2AE AE

× ×=



And RA + RB = 10 IES-43(i) Ans. (b) IES-44. Ans. (b) IES-45. Ans. (d) IES-46. Ans. (d) If we resist to expand then only stress will develop. IES-47. Ans. (d)

IES-48. Ans. (b) ( ) ( )33 3

3

1p a T aVV K a

σ α= + −Δ= =

( )

3

3 1 2

pOr TE

α

γ

=

−

IES-49. Ans. (c) IES-49(i). Ans. (c) IES-50. Ans. (d) ( ) ( ) ( )6 3E t 12 10 200 10 120 20 240MPaα −Δ = × × × × − = It will be compressive as elongation restricted. IES-51. Ans. (a) co-efficient of volume expansion ( ) ( )3 co efficient of linear expansionγ α= × − IES-52. Ans. (b) IES-53. Ans. (b) Let compression of the spring = x m Therefore spring force = kx kN Expansion of the rod due to temperature rise = L tαΔ

Reduction in the length due to compression force = ( )kx L

AE×

Now ( )kx L

L t xAE

α×

Δ − =

Or 6

26

0.5 12.5 10 20x 0.125mm

50 0.510.010 200 104

π

−× × ×= =⎧ ⎫⎪ ⎪×⎪ ⎪+⎨ ⎬×⎪ ⎪× ×⎪ ⎪⎩ ⎭

∴Compressive stress = 2

kx 50 0.125 0.07945MPaA 0.010

4π

×− = − = −⎛ ⎞×⎜ ⎟⎝ ⎠

IES-54. Ans. (d) Stress in the rod due to temperature rise = ( )t EαΔ × IES-55. Ans. (c) IES-56. Ans. (d) A is false but R is correct. IES-57. Ans. (d) IES-58. Ans. (b) IES-59. Ans. (d) IES-60. Ans. (b) IES-61. Ans. (a) IES-61(i). Ans. (a)

IES-62. Ans. (b) 2

c c2

W dor W4d

4

πσ σπ

= = × ;

2 2

csafe

dW 280 36W N 190kNfos fos 4 1.5 4

σ π π× × × ×= = = =× ×

IES-63. Ans. (b) IES-64. Ans. (a) A crack parallel to the direction of length of hub means the failure was due to tensile hoop

stress only. IES-65. Ans. (d) IES-66. Ans. (d)



IES-67. Ans. (c) IES-68. Ans. (c)

IAS

IAS-1. Ans. (d) Elongation due to self weight =( ) 2

2 2 2ALg LWL L g

AE AE Eδ δ= =

IAS-2. Ans. (b)

IAS-3. Ans. (a) The extension of the taper rod = 1 2

Pl

D D .E4π⎛ ⎞⎜ ⎟⎝ ⎠

IAS-4. Ans. (a) IAS-5. ans. (d) IAS-6. Ans. (b)

IAS-7. Ans. (d) Bulk modulus of elasticity (K) = 6v

v

P P 1.5or 535 10K 2800

εε

−= = = ×

IAS-8. Ans. (a) IAS-9. Ans. (d) IAS-10. Ans. (a) IAS-11. Ans.(b) )1(2 μ+= GE or 1.25x105 = 2G(1+0.34) or G = 0.4664 × 105 MPa

IAS-12. Ans. (a) ( ) E E 2.5E 2G 1 1 1 1 0.252G 2G 2

μ μ μ ⎛ ⎞ ⎛ ⎞= + ⇒ + = ⇒ = − = − =⎜ ⎟ ⎜ ⎟⎝ ⎠ ⎝ ⎠

IAS-13. Ans. (c) IAS-14. Ans. (b) E = 2G (1 + μ ) = 3k (1- 2 μ ) IAS-15. Ans. (b) E, G, K and µ represent the elastic modulus, shear modulus, bulk modulus and poisons

ratio respectively of a ‘linearly elastic, isotropic and homogeneous material.’ To express the stress – strain relations completely for this material; at least any two of the four must be

known. ( ) ( ) 92 1 3 1 33

KGE G KK G

μ μ= + = − =+

IAS-16. Ans. (c) E = 2G (1+ μ ) or μ =2001 1 0.25

2 2 80EG

− = − =×

IAS-17. Ans. (a) Elongation in AC = length reduction in CB

A BR 1 R 2AE AE

× ×=

And RA + RB = 10 IAS-18. Ans. (d) ( ) ( ) ( )6 3E t 12 10 200 10 120 20 240MPaα −Δ = × × × × − = It will be compressive as elongation restricted. IAS-19. Ans. (c) Thermal stress will develop only if expansion is restricted. IAS-20. Ans. (a) Dimensional analysis gives (a) is wrong IAS-21. Ans. (d) IAS-22. Ans. (d) IAS-23. Ans. (b)



IAS-24. Ans. (b) IAS-25. Ans. (b) IAS-26. Ans. (d) IAS-27. Ans. (d) IAS-28. Ans. (a) Up to elastic limit. IAS-29. Ans. (b) IAS-30. Ans. (d) IAS-31. Ans. (a) IAS-32. Ans. (a) IAS-33. Ans. (d) In compression tests of ductile materials fractures is seldom obtained. Compression is

accompanied by lateral expansion and a compressed cylinder ultimately assumes the shape of a flat disc.

IAS-34. Ans. (a) IAS-35. Ans. (c) Steel is the highly elastic material because it is deformed least on loading, and regains its

original from on removal of the load. IAS-36. Ans. (a) IAS-37. Ans. (a) IAS-38. Ans. (b) IAS-39. Ans. (b)



Previous Conventional Questions with Answers

Conventional Question IES-2010 Q. If a load of 60 kN is applied to a rigid

bar suspended by 3 wires as shown in the above figure what force will be resisted by each wire? The outside wires are of Al, cross- sectional area 300 mm2 and length 4 m. The central wire is steel with area 200 mm2 and length 8 m.

Initially there is no slack in the wires 5 2E 2 10 N / mm= × for Steel

5 20.667 10 N / mm= × for Aluminum

[2 Marks]

Ans.

FA1FSt

Aluminium wire

Steel wireFA1

60kN P 60 kN=

2A1 A1a 300mm l 4m= =

2st sta 200mm l 8m= =

5 2A1E 0.667 10 N / mm= ×

5 2stE 2 10 N / mm= ×

Force balance along vertical direction A1 st2F F 60 kN+ = (1) Elongation will be same in all wires because rod is rigid remain horizontal after loading

st stA1 A1

Al Al st st

F .lF la .E a .E

×= (2)

stA15 5

F 8F 4300 0.667 10 200 2 10

××=

× × × ×

A1 stF 1.0005 F= (3)

From equation (1) 3

st60 10F 19.99 kN or 20 kN3.001

×= =



A1F 20 kN=

A1

st

F 20 kNF 20 kN

= ⎫⎬= ⎭

Answer.

Conventional Question GATE Question: The diameters of the brass and steel segments of the axially loaded bar shown in

figure are 30 mm and 12 mm respectively. The diameter of the hollow section of the brass segment is 20 mm.

Determine: (i) The maximum normal stress in the steel and brass (ii) The displacement of the free end ; Take Es = 210 GN/m2 and Eb = 105 GN/m2

Answer: ( )2 2 6 2sA 12 36 mm 36 10 m

4π π π −= × = = ×

( ) ( )2 2 6 2b BC

A 30 225 mm 225 10 m4π π π −= × = = ×

( ) ( )2 2 2 6 2b CD

A 30 20 125 mm 125 10 m4π π π −= × − = = ×

(i) The maximum normal stress in steel and brass:

( )

( )

36 2 2

s 6

36 2 2

b 6BC

36 2 2

b 6CD

10 10 10 MN / m 88.42MN / m36 10

5 10 10 MN / m 7.07MN / m225 10

5 10 10 MN / m 12.73MN / m125 10

σπ

σπ

σπ

−−

−−

−−

×= × =×

×= × =×

×= × =×

(ii) The displacement of the free end:

( ) ( ) ( )s b bAB BC CD

9 6 9 6 9 6

5

l l l l

88.42 0.15 7.07 0.2 12.73 0.125 llE210 10 10 105 10 10 105 10 10

9.178 10 m 0.09178 mm

δ δ δ δ

σδ− − −

−

= + +

× × × ⎛ ⎞= + + =⎜ ⎟× × × × × × ⎝ ⎠= × =

∵

Conventional Question IES-1999 Question: Distinguish between fatigue strength and fatigue limit. Answer: Fatigue strength as the value of cyclic stress at which failure occurs after N cycles. And

fatigue limit as the limiting value of stress at which failure occurs as N becomes very large (sometimes called infinite cycle)

Conventional Question IES-1999 Question: List at least two factors that promote transition from ductile to brittle fracture. Answer: (i) With the grooved specimens only a small reduction in area took place, and the

appearance of the facture was like that of brittle materials.



(ii) By internal cavities, thermal stresses and residual stresses may combine with the effect of the stress concentration at the cavity to produce a crack. The resulting fracture will have the characteristics of a brittle failure without appreciable plastic flow, although the material may prove ductile in the usual tensile tests.

Conventional Question IES-1999 Question: Distinguish between creep and fatigue. Answer: Fatigue is a phenomenon associated with variable loading or more precisely to cyclic stressing

or straining of a material, metallic, components subjected to variable loading get fatigue, which leads to their premature failure under specific conditions.

When a member is subjected to a constant load over a long period of time it undergoes a slow permanent deformation and this is termed as ''Creep''. This is dependent on temperature.

Conventional Question IES-2008 Question: What different stresses set-up in a bolt due to initial tightening, while used as a

fastener? Name all the stresses in detail. Answer: (i) When the nut is initially tightened there will be some elongation in the bolt so tensile

stress will develop. (ii) While it is tightening a torque across some shear stress. But when tightening will be

completed there should be no shear stress. Conventional Question IES-2008 Question: A Copper rod 6 cm in diameter is placed within a steel tube, 8 cm external diameter

and 6 cm internal diameter, of exactly the same length. The two pieces are rigidly fixed together by two transverse pins 20 mm in diameter, one at each end passing through both rod and the tube.

Calculated the stresses induced in the copper rod, steel tube and the pins if the temperature of the combination is raised by 50oC.

[Take ES=210 GPa, 0.0000115 /os Cα = ; Ec=105 GPa, 0.000017 /o

c Cα = ] Answer:

( )σ σα α+ =Δ −c s

c sc s

tE E

22

2 3 2c

6Area of copper rod(A ) = 2.8274 104 4 100

π π −⎛ ⎞⎟⎜= = ×⎟⎜ ⎟⎜⎝ ⎠d m m

2 22

2 3 28 6Area of steel tube (A ) = 2.1991 104 4 100 100

π π −⎡ ⎤⎛ ⎞ ⎛ ⎞⎢ ⎥⎟ ⎟⎜ ⎜= − = ×⎟ ⎟⎜ ⎜⎢ ⎥⎟ ⎟⎜ ⎜⎝ ⎠ ⎝ ⎠⎢ ⎥⎣ ⎦

sd m m

in temperature, 50Δ = oRise t C

cFree expansion of copper bar= L tα

Free expansion of steel tube = sL tα

( )Difference in free expansion = c s L tα α−

( ) 6 -4= 17-11.5 ×10 50=2.75×10L Lm− × × A compressive force (P) exerted by the steel tube on the copper rod opposed the extra

expansion of the copper rod and the copper rod exerts an equal tensile force P to pull the steel



tube. In this combined effect reduction in copper rod and increase in length of steel tube equalize the difference in free expansions of the combined system.

Reduction in the length of copper rod due to force P Newton=

( ) ( )( )3 9 m2.8275 10 105 10C

c c

PL PLLA E −

= =× ×

Increase in length of steel tube due to force P

( )( )( )3 9

.2.1991 10 210 10S

s s

PL P LL mA E −

= =× ×

Difference in length is equated ( ) ( ) 42.75 10

c sL L L−+ = ×

( )( ) ( )( )

43 9 3 9

. 2.75 102.8275 10 105 10 2.1991 10 210 10

PL P L L−− −

+ = ×× × × ×

Or P = 49.695 kN

c 349695Stress in copper rod, MPa=17.58MPa

2.8275 10c

PA

σ −= =×

349695 in steel tube, MPa 22.6MPa

2.1991 10ss

PStressA

σ −= = =×

Since each of the pin is in double shear, shear stress in pins ( pinτ )

=( )2

49695 =79 MPa2 2 0.02

4π

=× ×pin

PA

Conventional Question IES-2002 Question: Why are the bolts, subjected to impact, made longer? Answer: If we increase length its volume will increase so shock absorbing capacity will increased. Conventional Question IES-2007 Question: Explain the following in brief: (i) Effect of size on the tensile strength (ii) Effect of surface finish on endurance limit. Answer: (i) When size of the specimen increases tensile strength decrease. It is due to the reason

that if size increases there should be more change of defects (voids) into the material which reduces the strength appreciably.

(ii) If the surface finish is poor, the endurance strength is reduced because of scratches present in the specimen. From the scratch crack propagation will start.

Conventional Question IES-2004 Question: Mention the relationship between three elastic constants i.e. elastic modulus (E),

rigidity modulus (G), and bulk modulus (K) for any Elastic material. How is the Poisson's ratio (μ ) related to these modulli?

Answer: 9

3KGE

K G=

+

9KGµ) = 2G(1+ µ) =

3K + G3 (1 2E K= −

Conventional Question IES-1996 Question: The elastic and shear moduli of an elastic material are 2×1011 Pa and 8×1010 Pa

respectively. Determine Poisson's ratio of the material.

Answer: We know that E = 2G(1+µ ) = 9KG3K(1- 2µ) =

3K + G



or µ

µ

11

10

or,12

2 101 1 0.252 2 (8 10 )

EG

EG

=

+ =

×− = − =

× ×

Conventional Question IES-2003 Question: A steel bolt of diameter 10 mm passes through a brass tube of internal diameter 15

mm and external diameter 25 mm. The bolt is tightened by a nut so that the length of tube is reduced by 1.5 mm. If the temperature of the assembly is raised by 40oC, estimate the axial stresses the bolt and the tube before and after heating. Material properties for steel and brass are:

5 5SE 2 10 / 1.2 10 /α −= × = × o

S C2N mm and Eb= 1×105 N/mm2 αb=1.9×10-5/oC Answer:

π

π

2 2 5 2s

2 2 4b

of steel bolt (A )= (0.010) 7.854 104

of brass tube (A )= (0.025) (0.015) 3.1416 104

Area m m

Area

−

−

× = ×

⎡ ⎤− = ×⎢ ⎥⎣ ⎦

Sσ σ

σ σσL

L

b

b. b

Stress due to tightening of the nut

Compressive force on brass tube= tensile fore on steel boltor,

( ), E . E=

b s

bs s

A A

lor A A

=

⎡ ⎤⎢ ⎥⎢ ⎥Δ⎢ ⎥= =

⎛ ⎞⎢ ⎥∈ ⎟⎜⎢ ⎥⎟⎜ ⎟⎜⎢ ⎥⎝ ⎠⎣ ⎦

∵

( )

35 6 4 -5

35

b.

assume total length ( )=1m(1.5 10 )Therefore (1×10 10 ) 3.1416 10 7.854×10

1600 ( )

( ) (1.5 10 )and =E (1×10 ) 150 ( )1

s

s

bb

Let

or MPa tensilel MPa MPa Compressive

σ

σ

σ

−−

−

×× × × × = ×

=

Δ ×= × =

σσ

b

s

before heating Stress in brass tube ( ) 150 ( ) Stress in steel bolt( ) 600 (tensile)

SoMPa compressive

MPa=

=

Stress due to rise of temperature Let stress ' '

bσ & σ s due to brass tube and steel bolt.are



If the two members had been free to expand, Free expansion of steel = s 1tα × ×

Free expansion of brass tube = 1α × ×b t

Since b s σα > free expansion of copper is greater than the free expansion of steel. But they are rigidly fixed so final expansion of each members will be same. Let us assume this final expansion is 'δ ', The free expansion of brass tube is grater than δ , while the free expansion of steel is less than δ . Hence the steel rod will be subjected to a tensile stress while the brass tube will be subjected to a compressive stress.

For the equilibrium of the whole system, Total tension (Pull) in steel =Total compression (Push) in brass tube.

'bσ σ σ σ σ σ

5' ' ' ' '

b s 4

7.854 10, 0.253.14 10

sb s s S S

b

AA A or

A

−

−

×= = × = =

×

( )

's

s

σE

σ σ

'b

sb

' '5 5

5 6 5 6

Final expansion of steel =final expansion of brass tube

( ).1 1 ( ) 1 1E

, 1.2 10 40 1 (1.9 10 ) 40 1 ( )2 10 10 1 10 10

b

s b

t t

or ii

σα α

− −

+ × = × − ×

× × × + = × × × − −−× × × ×

'sσ

σ

411 11

'

'b

From(i) & (ii) we get

1 0.25 2.8 102 10 10

, 37.33 MPa (Tensile stress)

or, σ = 9.33MPa (compressive)sor

−⎡ ⎤⎢ ⎥+ = ×⎢ ⎥×⎣ ⎦

=

'b b

's s

Therefore, the final stresses due to tightening and temperature rise Stress in brass tube =σ +σ =150+9.33MPa=159.33MPa

Stress in steel bolt =σ +σ = 600 + 37.33 = 637.33MPa.

Conventional Question IES-1997 Question: A Solid right cone of axial length h is made of a material having density ρ and

elasticity modulus E. It is suspended from its circular base. Determine its elongation due to its self weight.

Answer: See in the figure MNH is a solid right cone of length 'h' .

Let us assume its wider end of diameter’d’ fixed rigidly at MN.

Now consider a small strip of thickness dy at a distance y from the lower end.

Let 'ds' is the diameter of the strip.

π 21Weight of portion UVH= ( )

3 4sd

y g iρ⎛ ⎞⎟⎜ ⎟∴ × −⎜ ⎟⎜ ⎟⎜⎝ ⎠

From the similar triangles MNH and UVH,MNUV

., ( )

s

s

dd y

d yor d ii

= =

= −−−−



π 2

force at UV Weight of UVHStress at section UV =sec area at UV

4scross tion d

∴ =⎛ ⎞− ⎟⎜ ⎟⎜ ⎟⎜ ⎟⎜⎝ ⎠

π

π

2

2

1 . . . 13 4 =3

4

s

s

d y gy g

d

ρρ=

⎛ ⎞⎟⎜ ⎟⎜ ⎟⎜ ⎟⎜⎝ ⎠

h 2

0

1 .3, extension in dy=

13Total extension of the bar =

6

y g dySo

E

y gdy ghE E

ρ

ρ ρ

⎛ ⎞⎟⎜ ⎟⎜ ⎟⎜⎝ ⎠

∴ =∫

δ δd

From stress-strain relation ship.E= ,or dEδ

= =∈

Conventional Question IES-2004 Question: Which one of the three shafts listed hare has the highest ultimate tensile strength?

Which is the approximate carbon content in each steel? (i) Mild Steel (ii) cast iron (iii) spring steel Answer: Among three steel given, spring steel has the highest ultimate tensile strength. Approximate carbon content in (i) Mild steel is (0.3% to 0.8%) (ii) Cost iron (2% to 4%) (iii) Spring steel (0.4% to 1.1%) Conventional Question IES-2003 Question: If a rod of brittle material is subjected to pure torsion, show with help of a sketch,

the plane along which it will fail and state the reason for its failure. Answer: Brittle materials fail in tension. In a torsion test the maximum tensile test Occurs at 45° to

the axis of the shaft. So failure will occurs along a 45o to the axis of the shaft. So failure will occurs along a 45° helix

XX

So failures will occurs according to 45° plane. Conventional Question IAS-1995 Question: The steel bolt shown in Figure has a thread pitch of 1.6 mm. If the nut is initially

tightened up by hand so as to cause no stress in the copper spacing tube, calculate the stresses induced in the tube and in the bolt if a spanner is then used to turn the nut through 90°.Take Ec and Es as 100 GPa and 209 GPa respectively.

Answer: Given: p = 1.6 mm, Ec= 100 GPa ; Es = 209 CPa.



Stresses induced in the tube and the bolt, c s, :σ σ

25 2

s

2 25 2

s

10A 7.584 10 m4 1000

18 12A 14.14 10 m4 1000 1000

π

π

−

−

⎛ ⎞= × = ×⎜ ⎟⎝ ⎠⎡ ⎤⎛ ⎞ ⎛ ⎞= × − = ×⎢ ⎥⎜ ⎟ ⎜ ⎟⎝ ⎠ ⎝ ⎠⎢ ⎥⎣ ⎦

Tensile force on steel bolt, Ps = compressive force in copper tube, Pc = P Also, Increase in length of bolt + decrease in length of tube = axial displacement of nut

( ) ( )

( )

3s c

3s c

s s c c

35 9 5 9

s c

90i,e l l 1.6 0.4mm 0.4 10 m360

Pl Plor 0.4 10 l l lA E A E

100 1 1or P 0.4 101000 7.854 10 209 10 14.14 10 100 10

or P 30386NP P386.88MPa and 214.89MPaA A

δ δ −

−

−− −

+ = × = = ×

+ = × = =

⎛ ⎞ ⎡ ⎤× + = ×⎜ ⎟ ⎢ ⎥× × × × × ×⎝ ⎠ ⎣ ⎦=

∴ = =

∵

Conventional Question AMIE-1997 Question: A steel wire 2 m long and 3 mm in diameter is extended by 0·75 mm when a weight

W is suspended from the wire. If the same weight is suspended from a brass wire, 2·5 m long and 2 mm in diameter, it is elongated by 4 -64 mm. Determine the modulus of elasticity of brass if that of steel be 2.0 × 105 N / mm2

Answer: Given, sl = 2 m, ds = 3 mm, slδ = 0·75 mm; Es = 2·0 × 105 N / mm2; bl = 2.5 m, db

=2 mm bl 4.64mδ = m and let modulus of elasticity of brass = Eb

Hooke's law gives,PllAE

δ = [Symbol has usual meaning]

Case I: For steel wire:

( )

ss

s s

2 5

PllA E

P 2 1000or 0.75

13 2.0 104 2000

δ

π

=

× ×=⎛ ⎞× × × ×⎜ ⎟⎝ ⎠

---- (i)

Case II: For bass wire:



( )

bb

b b

2b

2b

PllA E

P 2.5 10004.64

2 E4

1or P 4.64 2 E4 2500

δ

π

π

=

× ×=

⎛ ⎞× ×⎜ ⎟⎝ ⎠

⎛ ⎞= × × × ×⎜ ⎟⎝ ⎠

---- (ii)

From (i) and (ii), we get

2 5 2

b

5 2b

1 10.75 3 2.0 10 4.64 2 E4 2000 4 2500

or E 0.909 10 N / mm

π π⎛ ⎞ ⎛ ⎞× × × × × = × × × ×⎜ ⎟ ⎜ ⎟⎝ ⎠ ⎝ ⎠

= ×

Conventional Question AMIE-1997 Question: A steel bolt and sleeve assembly is shown in figure below. The nut is tightened up

on the tube through the rigid end blocks until the tensile force in the bolt is 40 kN. If an external load 30 kN is then applied to the end blocks, tending to pull them apart, estimate the resulting force in the bolt and sleeve.

Answer: Area of steel bolt, 2

4 2b

25A 4.908 10 m1000

−⎛ ⎞= = ×⎜ ⎟⎝ ⎠

Area of steel sleeve, 2 2

3 2s

62.5 50A 1.104 10 m4 1000 1000π −⎡ ⎤⎛ ⎞ ⎛ ⎞= − = ×⎢ ⎥⎜ ⎟ ⎜ ⎟⎝ ⎠ ⎝ ⎠⎢ ⎥⎣ ⎦

Forces in the bolt and sleeve: (i) Stresses due to tightening the nut: Let bσ = stress developed in steel bolt due to tightening the nut; and sσ = stress developed in steel sleeve due to tightening the nut. Tensile force in the steel bolt = 40 kN = 0·04 MN

( )

b b4

b

2b 4

A 0.04

or 4.908 10 0.040.04 81.5MN / m tensile

4.908 10

σσ

σ

−

−

× =

× × =

∴ = =×

Compressive force in steel sleeve = 0·04 MN

( )

s s3

s

2s 3

A 0.04

or 1.104 10 0.040.04 36.23MN / m compressive

1.104 10

σσ

σ

−

−

× =

× × =

∴ = =×

(ii) Stresses due to tensile force:



Let the stresses developed due to tensile force of 30 kN = 0·03 MN in steel bolt and sleeve be b s' and 'σ σ respectively.

Then, b b s s' A ' A 0.03σ σ× + × =

4 3b s' 4.908 10 ' 1.104 10 0.03 (i)σ σ− −× × + × × = − − −

In a compound system with an external tensile load, elongation caused in each will be the same.

( )

( )

( )

bb b

b

bb b

b

ss s

s

b s

b s

b s

b s b s

'l lE'or l 0.5 Given,l 500mm 0.5

E'and l 0.4 Given,l 400mm 0.4

EBut l

' '0.5 0.4E E

or ' 0.8 ' Given,E E (2)

σδ

σδ

σδ

δ δσ σ

σ σ

= ×

= × = =

= × = =

=

∴ × = ×

= = − − −

Substituting this value in (1), we get

( )( )

( )

( )

4 3s s

2s

2b

2b b br

s s sr

0.8 ' 4.908 10 ' 1.104 10 0.03

gives ' 20MN / m tensile

and ' 0.8 20 16MN / m tensileResulting stress in steel bolt,

' 81.5 16 97.5MN / m

Resulting stress in steelsleeve,' 36.23 20 16.23MN /

σ σσ

σ

σ σ σ

σ σ σ

− −× × + × × =

=

= × =

= + = + =

= + = − = ( )( )

( )( )

( )

2

b br4

b sr3

m compressive

Resulting force in steel bolt, A

97.5 4.908 10 0.0478MN tensile

Resulting force in steelsleeve A

16.23 1.104 10 0.0179MN compressive

σ

σ

−

−

= ×

= × × =

= ×

= × × =


2. Principal Stress and Strain

Theory at a Glance (for IES, GATE, PSU) 2.1 States of stress

• Uni-axial stress: only one non-zero

principal stress, i.e. σ1 Right side figure represents Uni-axial state of

stress.

• Bi-axial stress: one principal stress

equals zero, two do not, i.e. σ1 > σ3 ; σ2 = 0Right side figure represents Bi-axial state of

stress.

• Tri-axial stress: three non-zero

principal stresses, i.e. σ1 > σ2 > σ3 Right side figure represents Tri-axial state of

stress.

• Isotropic stress: three principal

stresses are equal, i.e. σ1 = σ2 = σ3 Right side figure represents isotropic state of

stress.

• Axial stress: two of three principal

stresses are equal, i.e. σ1 = σ2 or σ2 = σ3 Right side figure represents axial state of

stress.


Chapter-2 Principal Stress and Strain S K Mondal’s • Hydrostatic pressure: weight of column of

fluid in interconnected pore spaces.

Phydrostatic = ρfluid gh (density, gravity, depth)

• Hydrostatic stress: Hydrostatic stress is

used to describe a state of tensile or

compressive stress equal in all directions

within or external to a body. Hydrostatic

stress causes a change in volume of a

material. Shape of the body remains

unchanged i.e. no distortion occurs in the

body. Right side figure represents Hydrostatic state of

stress.

Or

2.2 Uni-axial stress on oblique plane Let us consider a bar of uniform cross sectional area A under direct tensile load P giving rise to axial

normal stress P/A acting on a cross section XX. Now consider another section given by the plane YY inclined

at θ with the XX. This is depicted in following three ways.

Fig. (a)

Fig. (b)

Fig. (c)

Area of the YY Plane =θcos

A; Let us assume the normal stress in the YY plane is σ n and there is a

shear stress τ acting parallel to the YY plane.

Now resolve the force P in two perpendicular direction one normal to the plane YY = θcosP and another

parallel to the plane YY = Pcosθ


Chapter-2 Principal Stress and Strain S K Mondal’s

Therefore equilibrium gives, coscos

σ θθ

=nA P or

2cosnPA

σ θ=

and sincos

τ θθ

× =A P or sin cosτ θ θ= PA

or sin 2

2PA

τ θ=

• Note the variation of normal stress σ n and shear stress τ with the variation ofθ . When 0θ = ,

normal stress nσ is maximum i.e. ( )maxnPA

σ = and shear stress 0τ = . As θ is increased, the

normal stress nσ diminishes, until when 0, 0nθ σ= = . But if angle θ increased shear stress τ

increases to a maximum value max 2PA

τ = at 454

oπθ = = and then diminishes to 0τ = at 90oθ =

• The shear stress will be maximum when θ θ= =sin2 1 45oor

• And the maximum shear stress, max 2PA

τ =

• In ductile material failure in tension is initiated by shear stress i.e. the failure occurs across the

shear planes at 45o (where it is maximum) to the applied load.

Let us clear a concept about a common mistake: The angle θ is not between the applied load and the

plane. It is between the planes XX and YY. But if in any question the angle between the applied load and

the plane is given don’t take it asθ . The angle between the applied load and the plane is 90 - θ . In this

case you have to use the above formula as σ θ τ θ= − = −2cos (90 ) and sin(180 2 )2n

P PA A

where θ is the angle

between the applied load and the plane. Carefully observe the following two figures it will be clear.

Let us take an example: A metal block of 100 mm2 cross sectional area carries an axial tensile load of 10

kN. For a plane inclined at 300 with the direction of applied load, calculate:

(a) Normal stress

(b) Shear stress

(c) Maximum shear stress.

Answer: Here θ = − =90 30 60o o o

(a) Normal stress ( )σ θ ×= = × =3

2 22

10 10cos cos 60 25MPa100

on

P NA mm



(b) Shear stress ( )τ θ ×= = × =×

3

210 10sin2 sin120 43.3MPa

2 2 100oP N

A mm

(c) Maximum shear stress ( )τ ×= = =×

3

max 210 10 50MPa

2 2 100P NA mm

• Complementary stresses Now if we consider the stresses on an oblique plane Y’Y’ which is perpendicular to the previous plane YY. The stresses on this plane are known as complementary stresses. Complementary normal stress

is σ ′n and complementary shear stress isτ ′ . The following figure shows all the four stresses. To

obtain the stresses σ ′n and τ ′we need only to replace θ by 090θ + in the previous equation. The

angle 090θ + is known as aspect angle.

Therefore

( )2 2cos 90 sinon

P PA A

σ θ θ′ = + =

( )sin 2 90 sin 22 2

′ = + = −τ θ θoP PA A

It is clear σ σ′ + =n nPA

and τ τ′ = −

i.e. Complementary shear stresses are always equal in magnitude but opposite in sign.

• Sign of Shear stress For sign of shear stress following rule have to be followed:

The shear stress τ on any face of the element will be considered positive when it has a clockwise

moment with respect to a centre inside the element. If the moment is counter- clockwise with respect

to a centre inside the element, the shear stress in negative.


Chapter-2 Principal Stress and Strain S K Mondal’s Note: The convention is opposite to that of moment of force. Shear stress tending to turn clockwise is

positive and tending to turn counter clockwise is negative.

Let us take an example: A prismatic bar of 500 mm2 cross sectional area is axially loaded with a tensile force of 50 kN. Determine all the stresses acting on an element which makes 300 inclination with the

vertical plane.

Answer: Take an small element ABCD in 300 plane as shown in figure below,

Given, Area of cross-section, A = 500 mm2, Tensile force (P) = 50 kN

Normal stress on 30° inclined plane, ( )3

2 2n 2

P 50×10 Nσ = cos θ = ×cos 30 =75MPaA 500 mm

o (+ive means tensile). Shear

stress on 30° planes, ( ) ( )τ θ ×= = × × =×

3

250 10sin2 sin 2 30 43.3MPa

2 2 500oP N

A mm

(+ive means clockwise) Complementary stress on ( )θ = + =90 30 120o

Normal stress on 1200 inclined plane, ( )σ θ ×′ = = × =3

2 22

50 10cos cos 120 25MPa500

on

P NA mm

(+ ive means tensile)

Shear stress on 1200 nclined plane, ( ) ( )τ θ ×′ = = × × = −×

3

250 10sin2 sin 2 120 43.3MPa

2 2 500oP N

A mm

(- ive means counter clockwise)

State of stress on the element ABCD is given below (magnifying)


Chapter-2 Principal Stress and Strain S K Mondal’s 2.3 Complex Stresses (2-D Stress system) i.e. Material subjected to combined direct and shear stress We now consider a complex stress system below. The given figure ABCD shows on small element of

material

Stresses in three dimensional element

Stresses in cross-section of the element

xσ and yσ are normal stresses and may be tensile or compressive. We know that normal stress may come

from direct force or bending moment. xyτ is shear stress. We know that shear stress may comes from direct

shear force or torsion and xyτ and yxτ are complementary and

xyτ = yxτ

Let nσ is the normal stress and τ is the shear stress on a plane at angleθ .

Considering the equilibrium of the element we can easily get

( )Normal stress cos2 sin 22 2

x y x yn xy

σ σ σ σσ θ τ θ

+ −= + + and

( ) σ σShear stress 2θ - cos2θ

2x y

xysinτ τ−

=

Above two equations are coming from considering equilibrium. They do not depend on material properties

and are valid for elastic and in elastic behavior.

• Location of planes of maximum stress

(a) Normal stress, ( )maxnσ

For nσ maximum or minimum


Chapter-2 Principal Stress and Strain S K Mondal’s ( ) ( )

( ) ( ) ( ) xy

x

0, where cos2 sin22 2

2sin2 2 cos2 2 0 or tan2 =

2 ( )

x y x ynn xy

x yxy p

y

or

σ σ σ σσ σ θ τ θθ

σ σ τθ τ θ θ

σ σ

+ −∂= = + +

∂−

− × × + × =−

(b) Shear stress, maxτ

For τ maximum or minimum

0, where sin2 cos22

x yxy

σ στ τ θ τ θθ

−∂ = = −∂

( ) ( )σ σθ τ θ

τθ

σ σ

−× − − × =

−=

−

cos2 2 sin2 2 02

2cot 2

x yxy

xy

x y

or

or

Let us take an example: At a point in a crank shaft the stresses on two mutually perpendicular planes are 30 MPa (tensile) and 15 MPa (tensile). The shear stress across these planes is 10 MPa. Find the normal

and shear stress on a plane making an angle 300 with the plane of first stress. Find also magnitude and

direction of resultant stress on the plane.

Answer: Given ( ) ( )σ σ τ= + = + = 025MPa tensile , 15MPa tensile , 10MPa and 40x y xy

( )

( ) ( )


+ −= + +

+ −= + × + × =

Therefore, Normal stress cos2 sin22 230 15 30 15 cos 2 30 10sin 2 30 34.91 MPa

2 2

x y x yn xy

o o

( )

( ) ( )

σ στ θ τ θ

−= −

−= × − × =

Shear stress sin2 cos22

30 15 sin 2 30 10cos 2 30 1.5MPa2

x yxy

o o

( ) ( )

( )

στφ φ φσ

= + =

= = ⇒ =

2 2

0

Resultant stress 34.91 1.5 34.94MPa1.5and Obliquity , tan 2.46

34.91

r

n


Chapter-2 Principal Stress and Strain S K Mondal’s 2.4 Bi-axial stress Let us now consider a stressed element ABCD where τ xy =0, i.e. only σ x and σ y is there. This type of

stress is known as bi-axial stress. In the previous equation if you put τ xy =0 we get Normal stress, nσ and

shear stress, τ on a plane at angleθ .

• Normal stress , n 22 2

x y x y cosσ σ σ σ

σ θ+ −

= +

• Shear/Tangential stress, sin 22

x yσ στ θ

−=

• For complementary stress, aspect angle = 090θ +

• Aspect angle ‘θ ’ varies from 0 to /2π

• Normal stress varies between the valuesnσ

y( 0) & ( / 2)xσ θ σ θ π= =

Let us take an example: The principal tensile stresses at a point across two perpendicular planes are 100

MPa and 50 MPa. Find the normal and tangential stresses and the resultant stress and its obliquity on a

plane at 200 with the major principal plane

Answer: Given ( ) ( )σ σ θ= = = 0100MPa tensile , 50MPa tensile 20x y and

( ) ( )σ σ σ σσ θ

+ − + −= + = + × =100 50 100 50Normal stress, cos2 cos 2 20 94MPa2 2 2 2

x y x y on

( ) ( )( )

σ στ θ

σ

− −= = × =

= + =

0

2 2

100 50Shear stress, sin2 sin 2 20 16MPa2 2

Resultant stress 94 16 95.4MPa

x y

r

( ) τφσ

− −⎛ ⎞ ⎛ ⎞= = =⎜ ⎟ ⎜ ⎟⎝ ⎠⎝ ⎠

1 1 016Therefore angle of obliquity, tan tan 9.794n

• We may derive uni-axial stress on oblique plane from

cos2 sin 22 2

x y x yn xy


+ −= + +


Chapter-2 Principal Stress and Strain S K Mondal’s and σ σ

2θ - cos2θ2

x yxysinτ τ

−=

Just put σ = 0y and τ xy =0

Therefore,

( )σ σσ θ σ θ σ θ+ −= + = + = 20 0 1cos2 1 cos2 cos

2 2 2x x

n x x

and σ στ θ θ−

= =0 sin2 sin2

2 2x x

2.5 Pure Shear

• Pure shear is a particular case of bi-axial stress where x yσ σ= −

Note: orx yσ σ which one is compressive that is immaterial but one should be tensile and other

should be compressive and equal magnitude. If 100MPaxσ = then must be 100MPayσ − otherwise if

100MPayσ = then must be 100MPaxσ − .

• In case of pure shear on 45o planes

max xτ σ= ± ; 0 and 0n nσ σ ′= =

• We may depict the pure shear in an element by following two ways (a) In a torsion member, as shown below, an element ABCD is in pure shear (only shear stress is

present in this element) in this member at 45o plane an element ′ ′ ′ ′A B C D is also in pure shear

where σ σ= −x y but in this element no shear stress is there.

(b) In a bi-axial state of stress a member, as shown below, an element ABCD in pure shear where

σ σ= −x y but in this element no shear stress is there and an element ′ ′ ′ ′A B C D at 45o plane is

also in pure shear (only shear stress is present in this element).



Let us take an example: See the in the Conventional question answer section in this chapter and the question is “Conventional Question IES-2007”

2.6 Stress Tensor

• State of stress at a point ( 3-D) Stress acts on every surface that passes through the point. We can use three mutually perpendicular

planes to describe the stress state at the point, which we approximate as a cube each of the three planes

has one normal component & two shear components therefore, 9 components necessary to define stress

at a point 3 normal and 6 shear stress.

Therefore, we need nine components, to define the state of stress at a point

σ τ τσ τ τσ τ τ

x xy xz

y yx yz

z zx zy

For cube to be in equilibrium (at rest: not moving, not spinning)

τ ττ ττ τ

=

==

xy yx

xz zx

yz zy

If they don’t offset, block spins therefore,

only six are independent.

The nine components (six of which are independent) can be written in matrix form

11 12 13

21 22 23

31 32 33

orxx xy xz xx xy xz x xy xz

ij yx yy yz ij yx yy yz yx y yz

zx zy zz zx zy zz zx zy z

σ σ σ τ τ τ σ τ τ σ σ σσ σ σ σ τ τ τ τ τ σ τ σ σ σ

σ σ σ τ τ τ τ τ σ σ σ σ

⎛ ⎞ ⎛ ⎞ ⎛ ⎞ ⎛ ⎞⎜ ⎟ ⎜ ⎟ ⎜ ⎟ ⎜ ⎟= = = =⎜ ⎟ ⎜ ⎟ ⎜ ⎟ ⎜ ⎟

⎜ ⎟⎜ ⎟ ⎜ ⎟ ⎜ ⎟ ⎝ ⎠⎝ ⎠ ⎝ ⎠ ⎝ ⎠

This is the stress tensor Components on diagonal are normal stresses; off are shear stresses



• State of stress at an element (2-D)

2.7 Principal stress and Principal plane • When examining stress at a point, it is possible to choose three mutually perpendicular planes

on which no shear stresses exist in three dimensions, one combination of orientations for the three mutually perpendicular planes will cause the shear stresses on all three planes to go to zero this is

the state defined by the principal stresses.

• Principal stresses are normal stresses that are orthogonal to

each other

• Principal planes are the planes across which principal

stresses act (faces of the cube) for principal stresses (shear

stresses are zero)

• Major Principal Stress

2

21 2 2

x y x yxy

σ σ σ σσ τ

⎛ ⎞+ −= + +⎜ ⎟⎜ ⎟

⎝ ⎠

• Minor principal stress



2

22 2 2

x y x yxy

σ σ σ σσ τ

⎛ ⎞+ −= − +⎜ ⎟⎜ ⎟

⎝ ⎠

• Position of principal planes

xy

x

2tan2 =

( )py

τθ

σ σ−

• Maximum shear stress

2

21 2max 2 2

x yxy

σ σσ στ τ⎛ ⎞−−= = +⎜ ⎟⎜ ⎟⎝ ⎠

Let us take an example: In the wall of a cylinder the state of stress is given by, σ = 85MPa x

( )compressive , ( ) ( )σ τ= =25MPa tensile and shear stress 60MPay xy

Calculate the principal planes on which they act. Show it in a figure.

Answer: Given σ σ τ= − = =85MPa, 25MPa, 60MPax y xy

( ) σ σ σ σσ τ

+ −⎛ ⎞= + +⎜ ⎟

⎝ ⎠

− + − −⎛ ⎞= + + =⎜ ⎟⎝ ⎠

22

1

22

Major principal stress2 2

85 25 85 25 60 51.4MPa2 2

x y x yxy

( )

( )

σ σ σ σσ τ

+ −⎛ ⎞= − +⎜ ⎟

⎝ ⎠

− + − −⎛ ⎞= − +⎜ ⎟⎝ ⎠

= −

22

2

22

Minor principalstress2 2

85 25 85 25 602 2

111.4 MPa i.e. 111.4 MPa Compressive

x y x yxy

τθ

σ σ×= =

− − −

For principalplanes2 2 60tan2

85 25xy

Px y

θ σ

θ θ σ

= −

′ = + =

01

02

or 24 it is for

Complementary plane 90 66 it is for The Figure showing state of stress and principal stresses is given below

P

P P



The direction of one principle plane and the principle stresses acting on this would be σ 1 when is acting

normal to this plane, now the direction of other principal plane would be 900 + pθ because the principal

planes are the two mutually perpendicular plane, hence rotate the another plane 900 + pθ in the same

direction to get the another plane, now complete the material element as pθ is negative that means we are

measuring the angles in the opposite direction to the reference plane BC. The following figure gives clear

idea about negative and positive pθ .

2.8 Mohr's circle for plane stress • The transformation equations of plane stress can be represented in a graphical form which is

popularly known as Mohr's circle.

• Though the transformation equations are sufficient to get the normal and shear stresses on any

plane at a point, with Mohr's circle one can easily visualize their variation with respect to plane

orientation θ.

• Equation of Mohr's circle

We know that normal stress, cos 2 sin 22 2


+ −= + +x y x y

n xy

And Tangential stress, σ σ

τ 2θ - τ cos 2θ2

x yxysin

−=

Rearranging we get, cos 2 sin 22 2

σ σ σ σσ θ τ θ⎛ ⎞+ −

− = +⎜ ⎟⎜ ⎟⎝ ⎠

x y x yn xy ……………(i)



and σ σ

τ 2θ - τ cos 2θ2

x yxysin

−= ……………(ii)

A little consideration will show that the above two equations are the equations of a circle with σ n and τ as

its coordinates and 2θ as its parameter.

If the parameter 2θ is eliminated from the equations, (i) & (ii) then the significance of them will become

clear.

2σ σ

σ+

= x yavg and R =

2

2

2σ σ

τ⎛ ⎞−

+⎜ ⎟⎜ ⎟⎝ ⎠

x yxy

Or ( )2 2 2σ σ τ− + =n avg xy R

It is the equation of a circle with centre, ( ),0 . . ,02

x yavg i e

σ σσ

⎛ ⎞+⎜ ⎟⎜ ⎟⎝ ⎠

and radius,

2

2

2x y

xyRσ σ

τ⎛ ⎞−

= +⎜ ⎟⎜ ⎟⎝ ⎠

• Construction of Mohr’s circle

Convention for drawing • A xyτ that is clockwise (positive) on a face resides above the σ axis; a xyτ anticlockwise

(negative) on a face resides below σ axis.

• Tensile stress will be positive and plotted right of the origin O. Compressive stress will be

negative and will be plotted left to the origin O.

• An angle θ on real plane transfers as an angle 2θ on Mohr’s circle plane.

We now construct Mohr’s circle in the following stress conditions

I. Bi-axial stress when xσ and yσ known and xyτ = 0

II. Complex state of stress ( ,x yσ σ and xyτ known)

I. Constant of Mohr’s circle for Bi-axial stress (when only xσ and yσ known)

If xσ and yσ both are tensile or both compressive sign of xσ and yσ will be same and this state of stress

is known as “ like stresses” if one is tensile and other is compressive sign of xσ and yσ will be opposite and

this state of stress is known as ‘unlike stress’.

• Construction of Mohr’s circle for like stresses (when xσ and yσ are same type of stress)

Step-I: Label the element ABCD and draw all stresses.



Step-II: Set up axes for the direct stress (as abscissa) i.e., in x-axis and shear stress (as ordinate) i.e. in

Y-axis

Step-III: Using sign convention and some suitable scale, plot the stresses on two adjacent faces e.g. AB

and BC on the graph. Let OL and OM equal to xσ and yσ respectively on the axis Oσ .

Step-IV: Bisect ML at C. With C as centre and CL or CM as radius, draw a circle. It is the Mohr’s

circle.

Step-V: At the centre C draw a line CP at an angle2θ , in the same direction as the normal to the

plane makes with the direction of xσ . The point P represents the state of stress at plane ZB.



Step-VI: Calculation, Draw a perpendicular PQ and PR where PQ = τ and PR = σ n

OC and MC = CL = CP = 2 2

PR = cos 22 2

PQ = = CPsin 2 = sin 22

x y x y

x y x y

x y

n

σ σ σ σ

σ σ σ σσ θ

σ στ θ θ

+ −=

+ −= +

−

[Note: In the examination you only draw final figure (which is in Step-V) and follow the procedure step by step so that no mistakes occur.]

• Construction of Mohr’s circle for unlike stresses (when xσ and yσ are opposite in sign) Follow the same steps which we followed for construction for ‘like stresses’ and finally will get the figure

shown below.



Note: For construction of Mohr’s circle for principal stresses when ( 1σ and 2σ is known) then follow the

same steps of Constant of Mohr’s circle for Bi-axial stress (when only xσ and yσ known) just change the

1xσ σ= and 2yσ σ=

II. Construction of Mohr’s circle for complex state of stress ( xσ , yσ and xyτ known)

Step-I: Label the element ABCD and draw all stresses.

Step-II: Set up axes for the direct stress (as abscissa) i.e., in x-axis and shear stress (as ordinate) i.e. in

Y-axis



Step-III: Using sign convention and some suitable scale, plot the stresses on two adjacent faces e.g. AB

and BC on the graph. Let OL and OM equal to xσ and yσ respectively on the axis Oσ .

Draw LS perpendicular to oσ axis and equal to xyτ .i.e. LS= xyτ . Here LS is downward as

xyτ on AB face is (– ive) and draw MT perpendicular to oσ axis and equal to xyτ i.e. MT=

xyτ . Here MT is upward as xyτ BC face is (+ ive).

Step-IV: Join ST and it will cut oσ axis at C. With C as centre and CS or CT as radius, draw circle. It

is the Mohr’s circle.

Step-V: At the centre draw a line CP at an angle 2θ in the same direction as the normal to the plane

makes with the direction of xσ .



Step-VI: Calculation, Draw a perpendicular PQ and PR where PQ = τ and PR = σ n

Centre, OC = 2

x yσ σ+

Radius CS = ( ) ( )2

2 2 2CL LS CT= CP2

yx xyσ σ

τ−⎛ ⎞

+ = + =⎜ ⎟⎜ ⎟⎝ ⎠

PR cos 2 sin 22 2

PQ sin2 cos2 .2

x y x yn xy

x yxy


σ στ θ τ θ

+ −= = + +

−= = −

[Note: In the examination you only draw final figure (which is in Step-V) and follow the

procedure step by step so that no mistakes occur.]

Note: The intersections of oσ axis are two principal stresses, as shown below.

Let us take an example: See the in the Conventional question answer section in this chapter and the

question is “Conventional Question IES-2000”


Chapter-2 Principal Stress and Strain S K Mondal’s 2.9 Mohr's circle for some special cases: i) Mohr’s circle for axial loading:

; 0x y xyPA

σ σ τ= = =

ii) Mohr’s circle for torsional loading:

; 0xy x yTrJ

τ σ σ= = =

It is a case of pure shear iii) In the case of pure shear

(σ1 = - σ2 and σ3 = 0)

x yσ σ= −

maxτ σ= ± x iv) A shaft compressed all round by a hub

σ1 = σ2 = σ3 = Compressive (Pressure)


Chapter-2 Principal Stress and Strain S K Mondal’s v) Thin spherical shell under internal pressure

1 2 2 4σ σ= = =pr pD

t t (tensile)

vi) Thin cylinder under pressure

σ = =1 2pD pr

t t(tensile) and σ = =2 4 2

pd prt t

(tensile)

vii) Bending moment applied at the free end of a cantilever

Only bending stress, σ =1MyI

and σ τ= =2 0xy

2.10 Strain Normal strain Let us consider an element AB of infinitesimal length δx. After deformation of the actual body if

displacement of end A is u, that of end B is uu+ . x.x

δ∂∂

This gives an increase in length of element AB is

u uu+ . x -u xx x

δ δ∂ ∂⎛ ⎞=⎜ ⎟∂ ∂⎝ ⎠ and therefore the strain in x-direction is x

ux

ε ∂=∂

Similarly, strains in y and z directions are ywand .

x zzνε ε∂ ∂= =

∂ ∂

Therefore, we may write the three normal strain components

x yu w; ; andx y zz

νε ε ε∂ ∂ ∂= = =∂ ∂ ∂

.



Change in length of an infinitesimal element. Shear strain Let us consider an element ABCD in x-y plane and let the displaced position of the element be A B C D′ ′ ′ ′

.This gives shear strain in x-y plane as xyγ β=∝ + where ∝ is the angle made by the displaced live B C′ ′

with the vertical and β is the angle made by the displaced line A D′ ′ with the horizontal. This gives

u . y . xux xand =y y x x

νδ δ νβδ δ

∂ ∂∂ ∂∂ ∂∝ = = =∂ ∂

We may therefore write the three shear strain components as

xyγ yzu w;

x z yyν νγ∂ ∂ ∂ ∂= + = +

∂ ∂ ∂ ∂ and zx

w ux z

γ ∂ ∂= +∂ ∂

Therefore the state of strain at a point can be completely described by the six strain components and the strain components in their turns can be completely defined by the displacement components u,ν , and w.

Therefore, the complete strain matrix can be written as

0 0

0 0

u0 0

0 w

0

0

x

y

z

xy

yz

zx

x

y

z

x y

y z

z x

εεε

υγγγ

∂⎡ ⎤⎢ ⎥∂⎢ ⎥

∂⎢ ⎥⎧ ⎫ ⎢ ⎥∂⎪ ⎪ ⎢ ⎥⎪ ⎪ ∂⎢ ⎥ ⎧ ⎫⎪ ⎪ ⎢ ⎥∂⎪ ⎪ ⎪ ⎪= ⎢ ⎥⎨ ⎬ ⎨ ⎬∂ ∂⎢ ⎥⎪ ⎪ ⎪ ⎪

⎩ ⎭⎢ ⎥⎪ ⎪ ∂ ∂⎢ ⎥⎪ ⎪ ∂ ∂⎢ ⎥⎪ ⎪⎩ ⎭ ⎢ ⎥∂ ∂⎢ ⎥

∂ ∂⎢ ⎥⎢ ⎥∂ ∂⎣ ⎦


Chapter-2 Principal Stress and Strain S K Mondal’s Shear strain associated with the distortion of an infinitesimal element. Strain Tensor The three normal strain components are

x xx yu w; and x y zyy z zz

νε ε ε ε ε ε∂ ∂ ∂= = = = = =∂ ∂ ∂

.

The three shear strain components are

1 u 1 w 1 w; and 2 2 x 2 2 z y 2 2 zxy yz zx

xy yz zxu

y xγ γ γν ν⎛ ⎞⎛ ⎞∂ ∂ ∂ ∂ ∂ ∂⎛ ⎞∈ = = + ∈ = = + ∈ = = +⎜ ⎟⎜ ⎟ ⎜ ⎟∂ ∂ ∂ ∂ ∂ ∂⎝ ⎠⎝ ⎠ ⎝ ⎠

Therefore the strain tensor is

2 2

2 2

2 2

xy xzxx

xx xy xzyx yz

ij yx yy yz yy

zx zy zzzyzx

zz

γ γ

γ γ

γγ

⎡ ⎤∈⎢ ⎥

⎡ ⎤∈ ∈ ∈ ⎢ ⎥⎢ ⎥ ⎢ ⎥

∈ = ∈ ∈ ∈ = ∈⎢ ⎥ ⎢ ⎥⎢ ⎥ ⎢ ⎥∈ ∈ ∈⎣ ⎦ ⎢ ⎥

∈⎢ ⎥⎣ ⎦

Constitutive Equation The constitutive equations relate stresses and strains and in linear elasticity. We know from the Hook’s law ( ) E.σ ε=

Where E is modulus of elasticity

It is known that xσ produces a strain of E

xσ in x-direction

and Poisson’s effect gives E

xσμ− in y-direction and E

xσμ− in z-direction.

Therefore we my write the generalized Hook’s law as

( )1 σ μ σ σ⎡ ⎤∈ = − +⎣ ⎦x x y zE, ( )1 σ μ σ σ⎡ ⎤∈ = − +⎣ ⎦y y z xE

and ( )1 σ μ σ σ⎡ ⎤∈ = − +⎣ ⎦z z x yE

It is also known that the shear stress, Gτ γ= , where G is the shear modulus and γ is shear strain. We may

thus write the three strain components as

xy yz zxxy yz zx, and

G G Gτ τ τγ γ γ= = =

In general each strain is dependent on each stress and we may write

11 12 13 14 15 16

21 22 23 24 25 26

31 32 33 34 35 36

41 42 43 44 45 46

51 52 53 54 55 56

61 62 63 64 65 66

K K K K K KK K K K K KK K K K K KK K K K K KK K K K K KK K K K K K

x x

y y

z z

xy xy

yz yz

zx zx

ε σε σε σγ τγ τγ τ

⎧ ⎫ ⎧ ⎫⎡ ⎤⎪ ⎪ ⎪ ⎪⎢ ⎥⎪ ⎪ ⎪ ⎪⎢ ⎥⎪ ⎪ ⎪ ⎪⎢ ⎥⎪ ⎪ ⎪ ⎪⎢ ⎥=⎨ ⎬ ⎨ ⎬

⎢ ⎥⎪ ⎪ ⎪ ⎪⎢ ⎥⎪ ⎪ ⎪⎢ ⎥⎪ ⎪ ⎪⎢ ⎥⎪ ⎪ ⎪⎣ ⎦⎩ ⎭ ⎩ ⎭

⎪⎪⎪

∴ The number of elastic constant is 36 (For anisotropic materials)

For Anisotropic material only 21 independent elastic constant are there.

For isotropic material



11 22 33

44 55 66

12 13 21 23 31 32

1K K KE1K K K

K K K K K KE

Gμ

= = =

= = =

= = = = = = −

Rest of all elements in K matrix are zero. For isotropic material only two independent elastic constant is there say E and G.

• 1-D Stress

Let us take an example: A rod of cross sectional area Ao is loaded by a tensile force P.

It’s stresses , 0, 0Ax y z

o

P andσ σ σ= = =

1-D state of stress or Uni-axial state of stress

0 0 0 0 0 0

0 0 0 or 0 0 0 0 0 00 0 0 0 0 0 0 0 0

xx xx x

ij ij

σ τ σσ τ

⎛ ⎞ ⎛ ⎞ ⎛ ⎞⎜ ⎟ ⎜ ⎟ ⎜ ⎟= = =⎜ ⎟ ⎜ ⎟ ⎜ ⎟⎜ ⎟ ⎜ ⎟ ⎜ ⎟⎝ ⎠ ⎝ ⎠ ⎝ ⎠

Therefore strain components are

xx E

σ∈ = ; x

y xEσμ μ∈ = − = − ∈ ; and

xz xE

σμ μ∈ = − = − ∈

Strain

0 00 0 0 0

0 0 0 0 0 00 0 0 0

0 0

x

x yx

ij x y

x yx

E pq

Eq

E

σ

εσε με μ

με σμ

⎛ ⎞⎜ ⎟

⎛ ⎞⎜ ⎟⎛ ⎞⎜ ⎟⎜ ⎟ ⎜ ⎟= − = − = ⎜ ⎟⎜ ⎟ ⎜ ⎟

⎜ ⎟ ⎜ ⎟⎜ ⎟−⎝ ⎠ ⎝ ⎠⎜ ⎟−⎜ ⎟⎝ ⎠

• 2-D Stress ( 0)zσ =

(i) 1

x x yEσ μσ⎡ ⎤∈ = −⎣ ⎦

1

y y xEσ μσ⎡ ⎤∈ = −⎣ ⎦

μ σ σ⎡ ⎤∈ = − +⎣ ⎦z x yE

[Where, , ,x y z∈ ∈ ∈ are strain component in X, Y, and Z axis respectively]



(ii) 21x x yEσ μμ

⎡ ⎤= ∈ + ∈⎣ ⎦−

21y y xEσ μμ

⎡ ⎤= ∈ + ∈⎣ ⎦−

• 3-D Stress & Strain

(i) ( )1x x y zE

σ μ σ σ⎡ ⎤∈ = − +⎣ ⎦

( )1y y z xE

σ μ σ σ⎡ ⎤∈ = − +⎣ ⎦

( )1z z x yE

σ μ σ σ⎡ ⎤∈ = − +⎣ ⎦

(ii) ( )( ) ( ) ( )11 1 2x x y z

Eσ μ μμ μ

⎡ ⎤= − ∈ + ∈ + ∈⎣ ⎦+ −

( )( ) ( ) ( )

( )( ) ( ) ( )

11 1 2

11 1 2

y y z x

z z x y

E

E

σ μ μμ μ

σ μ μμ μ

⎡ ⎤= − ∈ + ∈ + ∈⎣ ⎦+ −

⎡ ⎤= − ∈ + ∈ + ∈⎣ ⎦+ −

Let us take an example: At a point in a loaded member, a state of plane stress exists and the strains are 6 6 6

x xy270 10 ; 90 10 and 360 10 .yε ε ε− − −= × = − × = × If the elastic constants E, μ and G are 200

GPa, 0.25 and 80 GPa respectively.

Determine the normal stress xσ and yσ and the shear stress xy

τ at the point.

Answer: We know that

.

{ }

{ }

ε σ μσ

ε σ μσ

τε

= −

= −

=

x x1E1E

G

y

y y x

xyxy

{ }σ ε μεμ

− −× ⎡ ⎤= + = + × − × ×⎣ ⎦− −=

96 6

x x y2 2E 200 10This gives 270 10 0.25 90 10 Pa

1 1 0.2552.8 MPa (i.e. tensile)



σ ε μεμ

τ ε

− −

−

⎡ ⎤= +⎣ ⎦−× ⎡ ⎤= − × + × × = −⎣ ⎦−

= = × × × =

x2

96 6

2

6 9xy xy

Eand 1200 10 90 10 0.25 270 10 Pa 4.8 MPa (i.e.compressive)1 0.25

and .G 360 10 80 10 Pa 28.8MPa

y y

2.12 An element subjected to strain components , &2xy

x y

γ∈ ∈

Consider an element as shown in the figure given. The strain component In X-direction is x∈ , the strain

component in Y-direction is y∈ and the shear strain component is xyγ .

Now consider a plane at an angle θ with X- axis in this plane a normal strain θ∈ and a shear strain θγ .

Then

• 2 sin 22 2 2

x y x y xycosθ

γθ θ

∈ + ∈ ∈ −∈∈ = + +

• 2 cos 22 2 2

x y xysinθ γγ θ θ∈ −∈

= − +

We may find principal strain and principal plane for strains in the same process which we followed for

stress analysis.

In the principal plane shear strain is zero.

Therefore principal strains are

2 2

1,2 2 2 2γ⎛ ⎞∈ + ∈ ∈ − ∈ ⎛ ⎞

∈ = ± +⎜ ⎟ ⎜ ⎟⎝ ⎠⎝ ⎠

x y x y xy

The angle of principal plane

tan 2( )

=∈ −∈

γθ xy

px y

• Maximum shearing strain is equal to the difference between the 2 principal strains i.e

max 1 2( )xyγ =∈ − ∈


Chapter-2 Principal Stress and Strain S K Mondal’s Mohr's Circle for circle for Plain Strain

We may draw Mohr’s circle for strain following same procedure which we followed for drawing Mohr’s

circle in stress. Everything will be same and in the place of xσ write x∈ , the place of yσ write y∈

and in place of xyτ write 2xyγ

.

2.15 Volumetric Strain (Dilation) • Rectangular block,

0x y z

VVΔ =∈ + ∈ + ∈

Proof: Volumetric strain

( ) ( ) ( )0 0

3

3

1 1 1ε ε ε

−Δ =

+ × + × + −=

=∈ + ∈ + ∈

o

x y z

x y z

V VVV V

L L L LL

(neglecting second and third order

term, as very small )

Before deformation,

Volume (Vo) = L3

After deformation,

Volume (V)

= ( ) ( ) ( )1 1 1x y zL L Lε ε ε+ × + × +


Chapter-2 Principal Stress and Strain S K Mondal’s • In case of prismatic bar,

Volumetric strain, ( )dv 1 2v

ε μ= −

Proof: Before deformation, the volume of the bar, V =

A.L

After deformation, the length ( ) ( )L 1L ε′ = +

and the new cross-sectional area ( ) ( )2A A 1 με′ = −

Therefore now volume ( ) ( ) ( )2A L =AL 1 1V ε με′ ′ ′= + −

( ) ( ) ( )

( )

2AL 1 1 ALV V -V 1 2V V AL

V 1 2V

ε μεε μ

ε μ

+ − −′Δ∴ = = = −

Δ = −

• Thin Cylindrical vessel

∈1=Longitudinal strain = [ ]1 2 1 22pr

E E Etσ σμ μ− = −

2∈ =Circumferential strain = [ ]2 1 22

− = −σ σμ μprE E Et

1 22 [5 4μ]2o

V prV EtΔ =∈ + ∈ = −

• Thin Spherical vessels

1 2 [1 ]2prEt

μ∈=∈ =∈ = −

0

33 [1 ]2

V prV Et

μΔ = ∈= −

• In case of pure shear

x yσ σ τ= − =

Therefore

( )

( )

x

y

z

1E

1E

0

τε μ

τε μ

ε

= +

= − +

=

x y zdvTherefore 0vvε ε ε ε= = + + =

2.16 Measurement of Strain Unlike stress, strain can be measured directly. The most common way of measuring strain is by use of the

Strain Gauge.



Strain Gauge

A strain gage is a simple device, comprising of a thin

electric wire attached to an insulating thin backing

material such as a bakelite foil. The foil is exposed to the

surface of the specimen on which the strain is to be

measured. The thin epoxy layer bonds the gauge to the

surface and forces the gauge to shorten or elongate as if it

were part of the specimen being strained.

A change in length of the gauge due to longitudinal strain

creates a proportional change in the electric resistance,

and since a constant current is maintained in the gauge, a

proportional change in voltage. (V = IR).

The voltage can be easily measured, and through calibration, transformed into the change in length of the

original gauge length, i.e. the longitudinal strain along the

gauge length.

Strain Gauge factor (G.F)

The strain gauge factor relates a change in resistance with strain.

Strain Rosette

The strain rosette is a device used to measure the state of strain at a point in a plane.

It comprises three or more independent strain gauges, each of which is used to read normal strain at the

same point but in a different direction.

The relative orientation between the three gauges is known as α , β and δ

The three measurements of normal strain provide sufficient information for the determination of the

complete state of strain at the measured point in 2-D.

We have to find out , ,x y xyand γ∈ ∈ form measured value , ,a b cand∈ ∈ ∈


Chapter-General The orienfigure. Tfollowing

2x

θ

∈ +∈ =

We get

2x

a

∈ +∈ =

2x

b

∈ +∈ =

2x

c

∈ +∈ =

From this

• Tw

-2 arrangeme

ntation of sTo relate s

formula.

2y x y∈ ∈ − ∈

+

2y x∈ ∈ − ∈

+

2y x∈ ∈ − ∈

+

2y x y∈ ∈ − ∈

+

s three equa

wo stand

(i) 45°

In the

0 ;oα =

Putting• ∈ =a

• ∈ =b

• ∈ =c

(ii) 60°

In the

0 ;oα =

Putting• a∈ =

• ∈ =b

• ∈ =c

Solving

ent: train gauge

strain we h

22

y cosγ

θ +

2y cosγ

α +

(2y cos α +

(2y cos α +

tions and th

dard arran

strain rose

general a

45o aβ =

g the value w=∈x

2γ∈ + ∈= +x x

=∈y

strain rose

general ar

60o aβ =

g the value wx=∈

34

∈ + ∈= +x y

34

∈ + ∈= −x y

above three

Principa

es is given have to us

sin22xyγ

θ

sin22xyγ

α

) sin2xyγ

β +

)2xyγ

β δ+ +

hree unknow

ngement

ette or Rec

arrangement

45oand δ =

we get

2γ xy

ette or Delt

rrangement

60oand δ =

we get

34

γ+ xy

34

γ− xy

e equation w

al Stress an

in the se the

( )n2 α β+

(sin2y α β+

wn we may s

of the of

ctangular st

t above, pu

ta strain ro

above, pu

we get

nd Strain

)β δ+

olve , ,x y∈ ∈

the strain

train roset

ut

osette

ut

or

4

xyand γ

n rosette

tte.

5o

60o

S K

are as fo

1200

Mondal’s

ollows:





Stresses at different angles and Pure Shear GATE-1. A block of steel is loaded by a tangential force on its top surface while the bottom

surface is held rigidly. The deformation of the block is due to [GATE-1992]

(a) Shear only (b) Bending only (c) Shear and bending (d) Torsion GATE-2. A shaft subjected to torsion experiences a pure shear stress τ on the surface. The

maximum principal stress on the surface which is at 45° to the axis will have a value [GATE-2003]

(a) τ cos 45° (b) 2τ cos 45° (c) τ cos2 45° (d) 2τ sin 45° cos 45° GATE-3. The number of components in a stress tensor defining stress at a point in three

dimensions is: [GATE-2002] (a) 3 (b) 4 (c) 6 (d) 9 GATE-3(i) In a two dimensional stress analysis, the state of stress at a point is shown below. If

120 MPa and 70MPa,σ = τ = and ,x yσ σ are respectively. [CE: GATE-2004]

A

B C x

y

σx

σy

στ

AB = 4BC = 3AC = 5

(a) 26.7 MPa and 172.5 MPa (b) 54 MPa and 128 MPa (c) 67.5 MPa and 213.3 MPa (d) 16 MPa and 138 MPa GATE-3(ii) The symmetry of stress tensor at a point in the body under equilibrium is obtained

from (a) conservation of mass (b) force equilibrium equations (c) moment equilibrium equations (d) conservation of energy [CE: GATE-2005]

Principal Stress and Principal Plane GATE-3(i) Consider the following statements: [CE: GATE-2009] 1. On a principal plane, only normal stress acts 2. On a principal plane, both normal and shear stresses act 3. On a principal plane, only shear stress acts 4. Isotropic state of stress is independent of frame of reference. Which of these statements is/are correct? (a) 1 and 4 (b) 2 only (c) 2 and 4 (d) 2 and 3


Chapter-2 Principal Stress and Strain S K Mondal’s GATE-3(ii)Consider the following statements: When a thick plate is subjected to external loads: 1. State of plane stress occurs at the surface 2. State of plane strain occurs at the surface 3. State of plane stress occurs in the interior part of the plate 4. State of plane strain occurs in the interior part of the plate Which of these statements are correct? [IES-2013] (a) 1 and 3 (b) 2 and 4 (c) 1 and 4 (d) 2 and 3 GATE-4. A body is subjected to a pure tensile stress of 100 units. What is the maximum shear

produced in the body at some oblique plane due to the above? [IES-2006] (a) 100 units (b) 75 units (c) 50 units (d) 0 unit GATE-5. In a strained material one of the principal stresses is twice the other. The maximum

shear stress in the same case is maxτ .Then, what is the value of the maximum principle stress? [IES 2007]

(a) maxτ (b) 2 maxτ (c) 4 maxτ (d) 8 maxτ GATE-5(i) If principal stresses in a two-dimensional case are –10 MPa and 20 MPa respectively,

then maximum shear stress at the point is [CE: GATE-2005] (a) 10 MPa (b) 15 MPa (c) 20 MPa (d) 30 MPa GATE-6. A material element subjected to a plane state of stress such that the maximum shear

stress is equal to the maximum tensile stress, would correspond to [IAS-1998]

GATE-7. A solid circular shaft is subjected to a maximum shearing stress of 140 MPs. The

magnitude of the maximum normal stress developed in the shaft is: [IAS-1995]

(a) 140 MPa (b) 80 MPa (c) 70 MPa (d) 60 MPa GATE-8. The state of stress at a point in a loaded member is shown in the figure. The

magnitude of maximum shear stress is [1MPa = 10 kg/cm2] [IAS 1994] (a) 10 MPa (b) 30 MPa (c) 50 MPa (d) 100MPa


Chapter-2 Principal Stress and Strain S K Mondal’s GATE-9. A solid circular shaft of diameter 100 mm is subjected to an axial stress of 50 MPa. It

is further subjected to a torque of 10 kNm. The maximum principal stress experienced on the shaft is closest to [GATE-2008]

(a) 41 MPa (b) 82 MPa (c) 164 MPa (d) 204 MPa GATE-9(i).The state of two dimensional stresses acting on a concrete lamina consists of a direct

tensile stress, 21.5 N/ mm ,xσ = and shear stress, 21.20 N/ mm ,τ = which cause cracking

of concrete. Then the tensile strength of the concrete in 2N/ mm is [CE: GATE-2003] (a) 1.50 (b) 2.08 (c) 2.17 (d) 2.29 GATE-10. In a bi-axial stress problem, the stresses in x and y directions are (σx = 200 MPa and σy

=100 MPa. The maximum principal stress in MPa, is: [GATE-2000] (a) 50 (b) 100 (c) 150 (d) 200 GATE-10(i)The state of plane stress at a point in a loaded member is given by: 800 MPaxσ = + 200 MPayσ = + 400 MPaxyτ = ± [IES-2013] The maximum principal stress and maximum shear stress are given by: (a) max max800 MPa and 400 MPaσ = τ = (b) max max800 MPa and 500 MPaσ = τ = (c) max max1000 MPa and 500 MPaσ = τ = (d) max max1000 MPa and 400 MPaσ = τ = GATE-11. The maximum principle stress for the stress

state shown in the figure is (a) σ (b) 2 σ (c) 3 σ (d) 1.5 σ

[GATE-2001]

GATE-12. The normal stresses at a point are σx = 10 MPa and, σy = 2 MPa; the shear stress at this point is 4MPa. The maximum principal stress at this point is:

[GATE-1998] (a) 16 MPa (b) 14 MPa (c) 11 MPa (d) 10 MPa GATE-13. In a Mohr's circle, the radius of the circle is taken as: [IES-2006; GATE-1993]

(a) ( )2

2

2x y

xy

σ στ

−⎛ ⎞+⎜ ⎟

⎝ ⎠ (b)

( ) ( )2

2

2x y

xy

σ στ

−+

(c) ( )2

2

2x y

xy

σ στ

−⎛ ⎞−⎜ ⎟

⎝ ⎠ (d) ( ) ( )2 2

x y xyσ σ τ− +

Where, σx and σy are normal stresses along x and y directions respectively and τxy is the shear stress.

GATE-14. A two dimensional fluid element rotates like a rigid body. At a point within the

element, the pressure is 1 unit. Radius of the Mohr's circle, characterizing the state of stress at that point, is: [GATE-2008]

(a) 0.5 unit (b) 0 unit (c) 1 unit (d) 2 units


Chapter-2 Principal Stress and Strain S K Mondal’s GATE-14(i). The state of stress at a point under plane stress condition is

σxx = 40 MPa, σyy = 100 MPa and τxy = 40 MPa. The radius of the Mohr’s circle representing the given state of stress in MPa is (a) 40 (b) 50 (c) 60 (d) 100 [GATE-2012]

GATE-14(ii) Mohr’s circle for the state of stress defined by 30 0 MPa0 30

⎡ ⎤⎢ ⎥⎣ ⎦

is a circle with

(a) center at (0, 0) and radius 30 MPa (b) center at (0, 0) and radius 60 MPa (c) center at (20, 0) and radius 30 MPa (d) center at (30, 0) and zero radius [CE: GATE-2006] GATE-15. The Mohr's circle of plane stress

for a point in a body is shown. The design is to be done on the basis of the maximum shear stress theory for yielding. Then, yielding will just begin if the designer chooses a ductile material whose yield strength is:

(a) 45 MPa (b) 50 MPa (c) 90 MPa (d) 100 MPa

[GATE-2005]

GATE-16. The figure shows the state of stress at a certain point in a stressed body. The magnitudes of normal stresses in the x and y direction are 100MPa and 20 MPa respectively. The radius of Mohr's stress circle representing this state of stress is:

(a) 120 (b) 80 (c) 60 (d) 40

[GATE-2004]

Data for Q17–Q18 are given below. Solve the problems and choose correct answers. [GATE-2003]

The state of stress at a point "P" in a two dimensional loading is such that the Mohr's circle is a point located at 175 MPa on the positive normal stress axis. GATE-17. Determine the maximum and minimum principal stresses respectively from the

Mohr's circle (a) + 175 MPa, –175MPa (b) +175 MPa, +175 MPa (c) 0, –175 MPa (d) 0, 0 GATE-18. Determine the directions of maximum and minimum principal stresses at the point

“P” from the Mohr's circle [GATE-2003] (a) 0, 90° (b) 90°, 0 (c) 45°, 135° (d) All directions

Principal strains GATE-19. If the two principal strains at a point are 1000 × 10-6 and -600 × 10-6, then the

maximum shear strain is: [GATE-1996] (a) 800 × 10-6 (b) 500 × 10-6 (c) 1600 × 10-6 (d) 200 × 10-6



Strain Rosette GATE-19(i)The components of strain tensor at a point in the plane strain case can be obtained

by measuring logitudinal strain in following directions. (a) along any two arbitrary directions (b) along any three arbitrary direction (c) along two mutually orthogonal directions (d) along any arbitrary direction [CE: GATE-2005]


Stresses at different angles and Pure Shear IES-1. If a prismatic bar be subjected to an axial tensile stress σ, then shear stress induced

on a plane inclined at θ with the axis will be: [IES-1992]

( ) ( ) ( ) ( )2 2a sin 2 b cos 2 c cos d sin 2 2 2 2σ σ σ σθ θ θ θ

IES-2. In the case of bi-axial state of normal stresses, the normal stress on 45° plane is equal

to [IES-1992] (a) The sum of the normal stresses (b) Difference of the normal stresses (c) Half the sum of the normal stresses (d) Half the difference of the normal stresses

IES-2a A point in two-dimensional stress state, is

subjected to biaxial stress as shown in the

above figure. The shear stress acting on

the plane AB is

(a) Zero (b) σ

(c) σ cos2 θ (d) σ sin θ. cos θ

σσ

σ

σ

B

A

θ

[IES-2010] IES-3. In a two-dimensional problem, the state of pure shear at a point is characterized by

[IES-2001] (a) 0x y xyandε ε γ= = (b) 0x y xyandε ε γ= − ≠

(c) 2 0x y xyandε ε γ= ≠ (d) 0.5 0x y xyandε ε γ= = IES-3a. What are the normal and shear stresses on

the 45o planes shown? 1 2

1 2

1 2

1 2

( ) 400 0( ) 400 0( ) 400 0( ) 200

a MPa andb MPa andc MPa andd MPa

σ σ τσ σ τσ σ τσ σ τ

= − = == = == = − == = = ±


Chapter-2 Principal Stress and Strain S K Mondal’s IES-4. Which one of the following Mohr’s circles represents the state of pure shear?

[IES-2000]

IES-5. For the state of stress of pure shear τ the strain energy stored per unit volume in the

elastic, homogeneous isotropic material having elastic constants E and ν will be: [IES-1998]

(a) ( )2

1Eτ ν+ (b) ( )

2

12Eτ ν+ (c) ( )

22 1Eτ ν+ (d) ( )

2

22Eτ ν+

IES-6. Assertion (A): If the state at a point is pure shear, then the principal planes through

that point making an angle of 45° with plane of shearing stress carries principal stresses whose magnitude is equal to that of shearing stress.

Reason (R): Complementary shear stresses are equal in magnitude, but opposite in direction. [IES-1996]

(a) Both A and R are individually true and R is the correct explanation of A (b) Both A and R are individually true but R is NOT the correct explanation of A (c) A is true but R is false (d) A is false but R is true IES-7. Assertion (A): Circular shafts made of brittle material fail along a helicoidally surface

inclined at 45° to the axis (artery point) when subjected to twisting moment. Reason (R): The state of pure shear caused by torsion of the shaft is equivalent to one

of tension at 45° to the shaft axis and equal compression in the perpendicular direction. [IES-1995]

(a) Both A and R are individually true and R is the correct explanation of A (b) Both A and R are individually true but R is NOT the correct explanation of A (c) A is true but R is false (d) A is false but R is true IES-8. A state of pure shear in a biaxial state of stress is given by [IES-1994]

(a) 1

2

00

σσ

⎛ ⎞⎜ ⎟⎝ ⎠

(b) 1

1

00

σσ

⎛ ⎞⎜ ⎟−⎝ ⎠

(c) x xy

yx y

σ ττ σ⎛ ⎞⎜ ⎟⎝ ⎠

(d) None of the above

IES-9. The state of plane stress in a plate of 100 mm thickness is given as [IES-2000] σxx = 100 N/mm2, σyy = 200 N/mm2, Young's modulus = 300 N/mm2, Poisson's ratio = 0.3.

The stress developed in the direction of thickness is: (a) Zero (b) 90 N/mm2 (c) 100 N/mm2 (d) 200 N/mm2

IES-10. The state of plane stress at a point is described by and 0x y xyσ σ σ τ= = = . The normal

stress on the plane inclined at 45° to the x-plane will be: [IES-1998] ( ) ( ) ( ) ( )a b 2 c 3 d 2 σ σ σ σ


Chapter-2 Principal Stress and Strain S K Mondal’s IES-10(i). An elastic material of Young’s modulus E and Poisson’s ratio ν is subjected to a

compressive stress of σ1 in the longitudinal direction. Suitable lateral compressive stress σ2 are also applied along the other two each of the lateral directions to half of the magnitude that would be under σ1 acting alone. The magnitude of σ2 is [IES-2012] ( ) ( + ) ( ) ( − ) ( ) ( + ) ( ) ( − )

IES-11. Consider the following statements: [IES-1996, 1998] State of stress in two dimensions at a point in a loaded component can be completely

specified by indicating the normal and shear stresses on 1. A plane containing the point 2. Any two planes passing through the point 3. Two mutually perpendicular planes passing through the point Of these statements (a) 1, and 3 are correct (b) 2 alone is correct (c) 1 alone is correct (d) 3 alone is correct IES-11a If the principal stresses and maximum shearing stresses are of equal numerical value

at a point in a stressed body, the state of stress can be termed as (a) Isotropic (b) Uniaxial [IES-2010] (c) Pure shear (d) Generalized plane state of stress

Principal Stress and Principal Plane IES-12. A body is subjected to a pure tensile stress of 100 units. What is the maximum shear

produced in the body at some oblique plane due to the above? [IES-2006] (a) 100 units (b) 75 units (c) 50 units (d) 0 unit IES-13. In a strained material one of the principal stresses is twice the other. The maximum

shear stress in the same case is max .τ Then, what is the value of the maximum principle stress? [IES 2007]

(a) maxτ (b) 2 maxτ (c) 4 maxτ (d) 8 maxτ IES-14. In a strained material, normal stresses on two mutually perpendicular planes are σx

and σy (both alike) accompanied by a shear stress τxy One of the principal stresses will be zero, only if [IES-2006]

(a) 2

x yxy

σ στ

×= (b) xy x yτ σ σ= × (c) xy x yτ σ σ= × (d) 2 2

xy x yτ σ σ= +

IES-15. The principal stresses σ1, σ2 and σ3 at a point respectively are 80 MPa, 30 MPa and –40 MPa. The maximum shear stress is: [IES-2001]

(a) 25 MPa (b) 35 MPa (c) 55 MPa (d) 60 MPa IES-15(i). A piece of material is subjected, to two perpendicular tensile stresses of 70 MPa and

10 MPa. The magnitude of the resultant stress on a plane in which the maximum shear stress occurs is [IES-2012] (a) 70 MPa (b) 60 MPa (c) 50 MPa (d) 10 MPa

IES-16. Plane stress at a point in a body is defined by principal stresses 3σ and σ. The ratio of

the normal stress to the maximum shear stresses on the plane of maximum shear stress is: [IES-2000]

(a) 1 (b) 2 (c) 3 (d) 4 IES-17. Principal stresses at a point in plane stressed element are 2500 kg/cmx yσ σ= = .

Normal stress on the plane inclined at 45o to x-axis will be: [IES-1993] (a) 0 (b) 500 kg/cm2 (c) 707 kg/cm2 (d) 1000 kg/cm2


Chapter-2 Principal Stress and Strain S K Mondal’s IES-18. If the principal stresses corresponding to a two-dimensional state of stress are 1σ

and 2σ is greater than 2σ and both are tensile, then which one of the following

would be the correct criterion for failure by yielding, according to the maximum shear stress criterion? [IES-1993]

( )1 2 1 2

1( ) ( ) ( ) ( ) 22 2 2 2 2 2

yp yp ypypa b c d

σ σ σσ σ σ σ σ σ−

= ± = ± = ± = ±

IES-19. For the state of plane stress. Shown the maximum and

minimum principal stresses are: (a) 60 MPa and 30 MPa (b) 50 MPa and 10 MPa (c) 40 MPa and 20 MPa (d) 70 MPa and 30 MPa

[IES-1992] IES-20. Normal stresses of equal magnitude p, but of opposite signs, act at a point of a

strained material in perpendicular direction. What is the magnitude of the resultant normal stress on a plane inclined at 45° to the applied stresses? [IES-2005]

(a) 2 p (b) p/2 (c) p/4 (d) Zero IES-21. A plane stressed element is subjected to the state of stress given by

2100 kgf/cmx xyσ τ= = and σy = 0. Maximum shear stress in the element is equal to

[IES-1997]

( ) ( ) ( ) ( )2 2 2 2a 50 3 kgf/cm b 1 00kgf/cm c 50 5 kgf/cm d 1 50kgf/cm

IES-22. Match List I with List II and select the correct answer, using the codes given below the lists: [IES-1995]

List I(State of stress) List II(Kind of loading)

Codes: A B C D A B C D (a) 1 2 3 4 (b) 2 3 4 1 (c)

2 4 3 1 (d) 3 4 1 2

Mohr's circle IES-22(i). Statement (I): Mohr’s circle of stress can be related to Mohr’s circle of strain by some

constant of proportionality. [IES-2012] Statement (II): The relationship is a function of yield strength of the material. (a) Both Statement (I) and Statement (II) are individually true and Statement (II) is the correct explanation of Statement (I)


Chapter-2 Principal Stress and Strain S K Mondal’s (b) Both Statement (I) and Statement (II) are individually true but Statement (II) is not the correct explanation of Statement (I) (c) Statement (I) is true but Statement (II) is false (d) Statement (I) is false but Statement (II) is true

IES-23. Consider the Mohr's circle shown

above: What is the state of stress

represented by this circle?

x y xy

x y xy

x y xy

x y xy

(a) 0, 0

(b) 0, 0

(c) 0, 0

(d) 0, 0

σ σ τσ σ τσ σ τσ σ τ

= ≠ =

+ = ≠

= = ≠

≠ = =

[IES-2008]

IES-24. For a general two dimensional stress system, what are the coordinates of the centre

of Mohr’s circle? [IES 2007]

(a) 2

yx σσ −, 0 (b) 0,

2yx σσ +

(c) 2

yx σσ +,0(d) 0,

2yx σσ −

IES-25. In a Mohr's circle, the radius of the circle is taken as: [IES-2006; GATE-1993]

(a) ( )2

2

2x y

xy

σ στ

−⎛ ⎞+⎜ ⎟

⎝ ⎠ (b)

( ) ( )2

2

2x y

xy

σ στ

−+

(c) ( )2

2

2x y

xy

σ στ

−⎛ ⎞−⎜ ⎟

⎝ ⎠ (d) ( ) ( )2 2

x y xyσ σ τ− +

Where, σx and σy are normal stresses along x and y directions respectively and τxy is the shear stress.

IES-26. Maximum shear stress in a Mohr's Circle [IES- 2008] (a) Is equal to radius of Mohr's circle (b) Is greater than radius of Mohr's circle (c) Is less than radius of Mohr's circle (d) Could be any of the above IES-27. At a point in two-dimensional stress system σx = 100 N/mm2, σy = τxy = 40 N/mm2. What

is the radius of the Mohr circle for stress drawn with a scale of: 1 cm = 10 N/mm2? [IES-2005]

(a) 3 cm (b) 4 cm (c) 5 cm (d) 6 cm IES-28. Consider a two dimensional state of stress given for an element as shown in the

diagram given below: [IES-2004]

What are the coordinates of the centre of Mohr's circle? (a) (0, 0) (b) (100, 200) (c) (200, 100) (d) (50, 0)


Chapter-2 Principal Stress and Strain S K Mondal’s IES-29. Two-dimensional state of stress at a point in a plane stressed element is represented

by a Mohr circle of zero radius. Then both principal stresses (a) Are equal to zero [IES-2003] (b) Are equal to zero and shear stress is also equal to zero (c) Are of equal magnitude but of opposite sign (d) Are of equal magnitude and of same sign IES-30. Assertion (A): Mohr's circle of stress can be related to Mohr's circle of strain by some

constant of proportionality. [IES-2002] Reason (R): The relationship is a function of yield stress of the material. (a) Both A and R are individually true and R is the correct explanation of A (b) Both A and R are individually true but R is NOT the correct explanation of A (c) A is true but R is false (d) A is false but R is true IES-31. When two mutually perpendicular principal stresses are unequal but like, the

maximum shear stress is represented by [IES-1994] (a) The diameter of the Mohr's circle (b) Half the diameter of the Mohr's circle (c) One-third the diameter of the Mohr's circle (d) One-fourth the diameter of the Mohr's circle IES-32. State of stress in a plane element is shown in figure I. Which one of the following

figures-II is the correct sketch of Mohr's circle of the state of stress? [IES-1993, 1996]

Figure-I Figure-II

Strain IES-33. A point in a two dimensional state of strain is subjected to pure shearing strain of

magnitude xyγ radians. Which one of the following is the maximum principal strain? [IES-2008]

(a) xyγ (b) xyγ / 2 (c) xyγ /2 (d) 2 xyγ IES-34. Assertion (A): A plane state of stress does not necessarily result into a plane state of

strain as well. [IES-1996] Reason (R): Normal stresses acting along X and Y directions will also result into

normal strain along the Z-direction. (a) Both A and R are individually true and R is the correct explanation of A (b) Both A and R are individually true but R is NOT the correct explanation of A (c) A is true but R is false (d) A is false but R is true IES-34a Assertion (A): A plane state of stress always results in a plane state of strain.

Reason (R): A uniaxial state of stress results in a three-dimensional state of strain. (a) Both A and R are individually true and R is the correct explanation of A (b) Both A and R are individually true but R is NOT the correct explanation of A (c) A is true but R is false [IES-2010] (d) A is false but R is true


Chapter-2 Principal Stress and Strain S K Mondal’s IES-34b Assertion (A): A state of plane strain always results in plane stress conditions.

Reason (R): A thin sheet of metal stretched in its own plane results in plane strain conditions. [IES-2010]

(a) Both A and R are individually true and R is the correct explanation of A (b) Both A and R are individually true but R is NOT the correct explanation of A (c) A is true but R is false (d) A is false but R is true

Principal strains IES-35. Principal strains at a point are 6100 10−× and 6200 10 .−− × What is the maximum shear

strain at the point? [IES-2006] (a) 300 × 10–6 (b) 200 × 10–6 (c) 150 × 10–6 (d) 100 × 10–6 IES-36. The principal strains at a point in a body, under biaxial state of stress, are 1000×10–6

and –600 × 10–6. What is the maximum shear strain at that point? [IES-2009]

(a) 200 × 10–6 (b) 800 × 10–6 (c) 1000 × 10–6 (d) 1600 × 10–6 IES-37. The number of strain readings (using strain gauges) needed on a plane surface to

determine the principal strains and their directions is: [IES-1994] (a) 1 (b) 2 (c) 3 (d) 4

Principal strain induced by principal stress IES-38. The principal stresses at a point in two dimensional stress system are σ 1 and σ 2 and

corresponding principal strains are 1ε and 2ε . If E and ν denote Young's modulus and Poisson's ratio, respectively, then which one of the following is correct?

[IES-2008]

[ ]

[ ] [ ]

σ ε σ ε νεν

σ ε νε σ ε νεν

= = +−

= − = −−

1 1 1 1 22

1 1 2 1 1 22

E(a) E (b)1

E(c) (d) E1

IES-39. Assertion (A): Mohr's construction is possible for stresses, strains and area moment of inertia. [IES-2009] Reason (R): Mohr's circle represents the transformation of second-order tensor. (a) Both A and R are individually true and R is the correct explanation of A. (b) Both A and R are individually true but R is NOT the correct explanation of A. (c) A is true but R is false. (d) A is false but R is true. IES-40. A rectangular strain rosette, shown

in figure, gives following reading in astrain measurement task, ε1 =1000×10-6 , ε2 =800×10-6

and ε3 =600×10-6

The direction of the major principal strain with respect to gauge l is (a) 0o (b) 15o

(c) 30o (d) 45o

[IES-2011]




Stresses at different angles and Pure Shear IAS-1. On a plane, resultant stress is inclined at an angle of 45o to the plane. If the normal

stress is 100 N /mm2, the shear stress on the plane is: [IAS-2003] (a) 71.5 N/mm2 (b) 100 N/mm2 (c) 86.6 N/mm2 (d) 120.8 N/mm2 IAS-2. Biaxial stress system is correctly shown in [IAS-1999]

IAS-3. The complementary shear stresses of

intensity τ are induced at a point in the material, as shown in the figure. Which one of the following is the correct set of orientations of principal planes with respect to AB?

(a) 30° and 120° (b) 45° and 135° (c) 60° and 150° (d) 75° and 165°

[IAS-1998] IAS-4. A uniform bar lying in the x-direction is subjected to pure bending. Which one of the

following tensors represents the strain variations when bending moment is about the z-axis (p, q and r constants)? [IAS-2001]

(a) 0 0

0 00 0

pyqy

ry

⎛ ⎞⎜ ⎟⎜ ⎟⎜ ⎟⎝ ⎠

(b) 0 0

0 00 0 0

pyqy

⎛ ⎞⎜ ⎟⎜ ⎟⎜ ⎟⎝ ⎠

(c) 0 0

0 00 0

pypy

py

⎛ ⎞⎜ ⎟⎜ ⎟⎜ ⎟⎝ ⎠

(d) 0 0

0 00 0

pyqy

qy

⎛ ⎞⎜ ⎟⎜ ⎟⎜ ⎟⎝ ⎠

IAS-5. Assuming E = 160 GPa and G = 100 GPa for a material, a strain tensor is given as:

[IAS-2001] 0.002 0.004 0.0060.004 0.003 00.006 0 0

⎛ ⎞⎜ ⎟⎜ ⎟⎜ ⎟⎝ ⎠

The shear stress, xyτ is: (a) 400 MPa (b) 500 MPa (c) 800 MPa (d) 1000 MPa

Principal Stress and Principal Plane IAS-6. A material element subjected to a plane state of stress such that the maximum shear

stress is equal to the maximum tensile stress, would correspond to [IAS-1998]



IAS-7. A solid circular shaft is subjected to a maximum shearing stress of 140 MPs. The

magnitude of the maximum normal stress developed in the shaft is: [IAS-1995] (a) 140 MPa (b) 80 MPa (c) 70 MPa (d) 60 MPa IAS-8. The state of stress at a point in a loaded member is shown in the figure. The

magnitude of maximum shear stress is [1MPa = 10 kg/cm2] [IAS 1994] (a) 10 MPa (b) 30 MPa (c) 50 MPa (d) 100MPa

IAS-9. A horizontal beam under bending has a maximum bending stress of 100 MPa and a

maximum shear stress of 20 MPa. What is the maximum principal stress in the beam? [IAS-2004]

(a) 20 (b) 50 (c) 50 + 2900 (d) 100 IAS-10. When the two principal stresses are equal and like: the resultant stress on any plane

is: [IAS-2002] (a) Equal to the principal stress (b) Zero (c) One half the principal stress (d) One third of the principal stress IAS-11. Assertion (A): When an isotropic, linearly elastic material is loaded biaxially, the

directions of principal stressed are different from those of principal strains. Reason (R): For an isotropic, linearly elastic material the Hooke's law gives only two

independent material properties. [IAS-2001] (a) Both A and R are individually true and R is the correct explanation of A (b) Both A and R are individually true but R is NOT the correct explanation of A (c) A is true but R is false (d) A is false but R is true IAS-12. Principal stress at a point in a stressed solid are 400 MPa and 300 MPa respectively.

The normal stresses on planes inclined at 45° to the principal planes will be: [IAS-2000]

(a) 200 MPa and 500 MPa (b) 350 MPa on both planes (c) 100MPaand6ooMPa (d) 150 MPa and 550 MPa IAS-13. The principal stresses at a point in an elastic material are 60N/mm2 tensile, 20 N/mm2

tensile and 50 N/mm2 compressive. If the material properties are: µ = 0.35 and E = 105 Nmm2, then the volumetric strain of the material is: [IAS-1997]

(a) 9 × 10–5 (b) 3 × 10-4 (c) 10.5 × 10–5 (d) 21 × 10–5



Mohr's circle IAS-14. Match List-I (Mohr's Circles of stress) with List-II (Types of Loading) and select the

correct answer using the codes given below the lists: [IAS-2004] List-I List-II (Mohr's Circles of Stress) (Types of Loading)

1. A shaft compressed all round by a hub

2. Bending moment applied at the free

end of a cantilever

3. Shaft under torsion

4. Thin cylinder under pressure 5. Thin spherical shell under internal

pressure Codes: A B C D A B C D (a) 5 4 3 2 (b) 2 4 1 3 (c) 4 3 2 5 (d) 2 3 1 5 IAS-15. The resultant stress on a certain plane makes an angle of 20° with the normal to the

plane. On the plane perpendicular to the above plane, the resultant stress makes an angle of θ with the normal. The value of θ can be: [IAS-2001]

(a) 0° or 20° (b) Any value other than 0° or 90° (c) Any value between 0° and 20° (d) 20° only IAS-16. The correct Mohr's stress-circle drawn for a point in a solid shaft compressed by a

shrunk fit hub is as (O-Origin and C-Centre of circle; OA = σ1 and OB = σ2) [IAS-2001]

IAS-17. A Mohr's stress circle is drawn for a body subjected to tensile stress xf and yf in

two mutually perpendicular directions such that xf > yf . Which one of the following statements in this regard is NOT correct? [IAS-2000]

(a) Normal stress on a plane at 45° to xf is equal to 2

x yf f+

(b) Shear stress on a plane at 45° to xf is equal to 2

x yf f−

(c) Maximum normal stress is equal to xf .



(d) Maximum shear stress is equal to 2

x yf f+

IAS-18. For the given stress condition xσ =2 N/mm2, xσ =0 and 0xyτ = , the correct Mohr’s circle is: [IAS-1999]

IAS-19. For which one of the following two-dimensional states of stress will the Mohr's stress

circle degenerate into a point? [IAS-1996]

Principal strains IAS-20. In an axi-symmetric plane strain problem, let u be the radial displacement at r. Then

the strain components , ,r eθ θε ε ϒ are given by [IAS-1995]

(a) 2

, ,r ru u ur r rθ θε ε

θ∂ ∂= = ϒ =∂ ∂ ∂

(b) , ,r ru u or rθ θε ε∂= = ϒ =

∂

(c) , , 0r ru ur rθ θε ε ∂= = ϒ =

∂ (d)

2

, ,r ru u ur rθ θε ε

θ θ∂ ∂ ∂= = ϒ =∂ ∂ ∂ ∂

IAS-21. Assertion (A): Uniaxial stress normally gives rise to triaxial strain. Reason (R): Magnitude of strains in the perpendicular directions of applied stress is

smaller than that in the direction of applied stress. [IAS-2004] (a) Both A and R are individually true and R is the correct explanation of A (b) Both A and R are individually true but R is NOT the correct explanation of A (c) A is true but R is false (d) A is false but R is true IAS-22. Assertion (A): A plane state of stress will, in general, not result in a plane state of

strain. [IAS-2002] Reason (R): A thin plane lamina stretched in its own plane will result in a state of

plane strain. (a) Both A and R are individually true and R is the correct explanation of A (b) Both A and R are individually true but R is NOT the correct explanation of A (c) A is true but R is false (d) A is false but R is true



OBJECTIVE ANSWERS

GATE-1. Ans. (a) It is the definition of shear stress. The force is applied tangentially it is not a point load so you cannot compare it with a cantilever with a point load at its free end.

GATE-2. Ans. (d) x y x yn xycos2 sin2

2 2σ σ σ σ

σ θ τ θ+ −

= + +

Here ox 2 xy0, , 45σ σ τ τ θ= = = =

GATE-3. Ans. (d) It is well known that,

xy yx, xz zx yz zy

x y z xy yz zx

and

so that the state of stress at a point is given by six components , , and , ,

τ τ τ τ τ τσ σ σ τ τ τ

= = =

GATE-3(i) Ans. (c) Let ∠ = θCAB

∴ θ = θ = θ =3 4 3sin ; cos ; tan5 5 4

A

B C x

y

σx

σy

σθθ

τ

3

5

4

Thus from force equilibrium, σ × = × σ θ − τ θAB AC ( cos sin )x

⇒ ⎛ ⎞σ = × × − ×⎜ ⎟⎝ ⎠

5 4 3120 704 5 5x

⇒ σ = 67.5 MPax And, σ × = × σ θ + τ θBC AC ( sin cos )y

⇒ ⎛ ⎞σ = × × + ×⎜ ⎟⎝ ⎠

5 3 4120 703 5 5y

⇒ σ = 213.3 MPay GATE-3(ii) Ans. (c)



d2

d2

d2

d2

σy

σy

σx σx

τyx

τyx

τxy

τxy

Taking moment equilibrium about the centre, we get

τ × + τ × = τ × + τ ×2 2 2 2yx yx xy xyd d d d

∴ τ = τxy yx GATE-3(i) Ans. (a) On a principal plane, only normal stresses act. No shear stresses act on the principal

plane. GATE-3(ii) Ans. (a)

GATE-4. Ans. (c) 1 2max

100 0 50 units.2 2

σ στ − −= = =

GATE-5. Ans. (c) 2

21max

σστ −= , 21 2σσ = or 2

2max

στ = or max2 2τσ = or 21 2σσ = = max4τ

GATE-5(i) Ans. (b)

Maximum shear stress = σ − σ1 2

2

− −= =20 ( 10) 15 MPa2

GATE-6. Ans. (d) 1 2 1 1max 1

( )2 2

σ σ σ στ σ− − −= = =

GATE-7. Ans. (a) 1 2max 2

σ στ −= Maximum normal stress will developed if 1 2σ σ σ= − =

GATE-8. Ans. (c) 22

max 2 xyyx τ

σστ +⎟⎟

⎠

⎞⎜⎜⎝

⎛ −= = 2

2

302

4040 +⎟⎠⎞

⎜⎝⎛ −−

= 50 MPa

GATE-9. Ans. (b) Shear Stress (τ )= MPaPadT 93.50

)1.0(100001616

33 =××=

ππ

Maximum principal Stress = 22

22τσσ +⎟

⎠⎞

⎜⎝⎛+ bb =82 MPa

GATE-9(i) Ans. (c) Maximum principal stress

σ σ⎛ ⎞ ⎛ ⎞= + + τ = + + =⎜ ⎟ ⎜ ⎟⎝ ⎠ ⎝ ⎠

2 22 2 21.5 1.5 (1.20) 2.17 N/ mm

2 2 2 2x x

GATE-10. Ans. (d)2

x y x y 21 xy xyif 0

2 2σ σ σ σ

σ τ τ+ −⎛ ⎞

= + + =⎜ ⎟⎝ ⎠



2

x y x yx2 2

σ σ σ σσ

+ −⎛ ⎞= + =⎜ ⎟

⎝ ⎠

GATE-10(i). Ans. (c) GATE-11. Ans. (b) x y xy, ,σ σ σ σ τ σ= = =

( ) ( )2

2x y x y 2 21 xymax

0 22 2 2

σ σ σ σ σ σσ τ σ σ+ −⎛ ⎞ +∴ = + + = + + =⎜ ⎟

⎝ ⎠

GATE-12. Ans. (c) 2

x y x y 21 xy2 2

σ σ σ σσ τ

+ −⎛ ⎞= + +⎜ ⎟

⎝ ⎠

2210 2 10 2 4 11.66 MPa

2 2+ −⎛ ⎞= + + =⎜ ⎟

⎝ ⎠

GATE-13. Ans. (a)

GATE-14. Ans. (b) GATE-14(i). Ans. (b)

( )2

240 100 40 502

MPa−⎛ ⎞ + =⎜ ⎟⎝ ⎠

GATE-14(ii) Ans.(d) The maximum and minimum principal stresses are same. So, radius of circle becomes zero and

centre is at (30, 0). The circle is respresented by a point. GATE-15. Ans. (c)

1 2

y1 2max

1 2 y y

Given 10 MPa, 100 MPa

Maximum shear stress theory give2 2

or 10 ( 100) 90MPa

σ σσσ στ

σ σ σ σ

= − = −

−= =

− = ⇒ = − − − =

GATE-16. Ans. (c)

( )σ σ

σ σ

= = −

− − −= = =

x y

x y

100MPa, 20MPa

100 20Radius of Mohr 'scircle 60

2 2

GATE-17. Ans. (b)

1 2 x y 175 MPaσ σ σ σ= = = = +

GATE-18. Ans. (d) From the Mohr’s circle it will give all directions. GATE-19. Ans. (c) Shear strain ( ){ } 6 6

max mine e 1000 600 10 1600 10− −− = − − × = × GATE-19(i) Ans.(b)


Chapter-2 Principal Stress and Strain S K Mondal’s When strain is measured along any three arbitrary directions, the strain diagram is called

rosette.

IES IES-1. Ans. (a)

IES-2. Ans. (c) x y x yn xycos2 sin2

2 2σ σ σ σ

σ θ τ θ+ −

= + +

x yoxy nAt 45 and 0;

2σ σ

θ τ σ+

= = =

IES-2a Ans. (a) ( )τ τ−

=σ σ

Shear stress 2θ - cos2θ2

x yxysin

τ= = =Hereσ σ , σ σ 0x y xyand IES-3. Ans. (b) IES-3a. Ans. (a) IES-4. Ans. (c) IES-5. Ans. (a) 1 2 3, , 0σ τ σ τ σ= = − =

( ) ( ) μτ τ μτ τ τ+⎡ ⎤= + − − − =⎣ ⎦22 21 1U 2 V V

2E E

IES-6. Ans. (b) IES-7. Ans. (a) Both A and R are true and R is correct explanation for A. IES-8. Ans. (b) 1 2 3, , 0σ τ σ τ σ= = − = IES-9. Ans. (a)

IES-10. Ans. (a) x y x yn xycos2 sin2

2 2σ σ σ σ

σ θ τ θ+ −

= + +

IES-10(i). Ans. (b) IES-11. Ans. (d) IES-11a Ans. (c)

IES-12. Ans. (c) 1 2max

100 0 50 units.2 2

σ στ − −= = =

IES-13. Ans. (c) 2

21max

σστ −= , 21 2σσ = or 2

2max

στ = or max2 2τσ = or 21 2σσ = = max4τ

IES-14. Ans. (c) 2

x y x y 21,2 xy2 2

σ σ σ σσ τ

+ −⎛ ⎞= + +⎜ ⎟

⎝ ⎠

2x y x y 2

2 xy

2 2x y x y 2

xy xy x y

if 02 2

or or2 2

σ σ σ σσ τ

σ σ σ στ τ σ σ

+ −⎛ ⎞= ⇒ = +⎜ ⎟

⎝ ⎠

+ −⎛ ⎞ ⎛ ⎞= + = ×⎜ ⎟ ⎜ ⎟

⎝ ⎠ ⎝ ⎠

IES-15. Ans. (d) 1 2max

80 ( 40) 602 2

σ στ − − −= = = MPa

IES-15(i). Ans. (c)

IES-16. Ans. (b) xy

x y

2tan2 0

τθ θ

σ σ= ⇒ =

−

1 2max

32 2

σ σ σ στ σ− −= = =

Major principal stress on the plane of maximum shear = 13 2

2σ σσ σ+= =


Chapter-2 Principal Stress and Strain S K Mondal’s IES-17. Ans. (b) When stresses are alike, then normal stress σn on plane inclined at angle 45° is

2 22 2 21 1 1 1cos sin 500 500 kg/cm

2 22 2n y x y xσ σ θ σ θ σ σ⎛ ⎞ ⎛ ⎞ ⎡ ⎤= + = + = + =⎜ ⎟ ⎜ ⎟ ⎢ ⎥⎣ ⎦⎝ ⎠ ⎝ ⎠

IES-18. Ans. (a)

IES-19. Ans. (d)2

x y x y 21,2 xy2 2

σ σ σ σσ τ

+ −⎛ ⎞= + +⎜ ⎟

⎝ ⎠

2

21,2

50 ( 10) 50 10 402 2

σ + − +⎛ ⎞= + +⎜ ⎟⎝ ⎠

max min70 and 30σ σ= = −

IES-20. Ans. (d) x y x yx cos2

2 2σ σ σ σ

σ θ+ −

= +

nP P P P cos2 45 0

2 2σ − += + × =

IES-21. Ans. (c) ( )2

21,2

0 0 50 50 52 2

σ σσ τ+ +⎛ ⎞= ± + =⎜ ⎟⎝ ⎠

∓x xxy

Maximum shear stress = ( ) ( )1 2 50 5

2σ σ−

=

IES-22. Ans. (c) IES-22(i). Ans. (c) IES-23. Ans. (b) It is a case of pure shear. 1 2Just put σ σ= − IES-24. Ans. (c) IES-25. Ans. (a)

IES-26. Ans. (a)


Chapter-2 Principal Stress and Strain S K Mondal’s 2

2 2x y x y2 2

x x y xy

2x y 2

xy

2x y x y 2

t xy

2x y x y 2

2 xy

x y1 2max max

2 2

Radius of the Mohr Circle

2

2 2

2 2

r 2 2

′ ′ ′

⎛ ⎞σ + σ σ − σ⎛ ⎞ ⎛ ⎞⎜ ⎟σ − + τ = + τ⎜ ⎟ ⎜ ⎟⎜ ⎟ ⎜ ⎟⎜ ⎟⎜ ⎟⎝ ⎠ ⎝ ⎠⎝ ⎠∴

σ − σ⎛ ⎞+ τ⎜ ⎟⎜ ⎟

⎝ ⎠

σ + σ σ − σ⎛ ⎞∴ σ = + + τ⎜ ⎟⎜ ⎟

⎝ ⎠

σ + σ σ − σ⎛ ⎞σ = − + τ⎜ ⎟⎜ ⎟

⎝ ⎠

σ − σ⎛ ⎞σ − σ⇒ τ = = ⇒ τ = ⎜⎜

⎝

22xy+ τ⎟⎟

⎠

IES-27. Ans. (c) Radius of the Mohr circle

2 2

x y 2 2xy

100 40/ 10 40 / 10 50 / 10 5cm2 2

σ στ

⎡ ⎤ ⎡ ⎤−⎛ ⎞ −⎛ ⎞⎢ ⎥ ⎢ ⎥= + = + = =⎜ ⎟ ⎜ ⎟⎢ ⎥ ⎢ ⎥⎝ ⎠⎝ ⎠ ⎣ ⎦⎣ ⎦

IES-28. Ans. (d) Centre of Mohr’s circle is ( )x y 200 100,0 ,0 50,02 2

σ σ+⎛ ⎞ −⎛ ⎞= =⎜ ⎟ ⎜ ⎟⎝ ⎠⎝ ⎠

IES-29. Ans. (d) IES-30. Ans. (c) IES-31. Ans. (b) IES-32. Ans. (c) IES-33. Ans. (c) IES-34. Ans. (a) IES-34a. Ans. (d) IES-34b. Ans. (d) IES-35. Ans. (a) ( ) 6 6

max 1 2 100 200 10 300 10γ ε ε − −= − = − − × = ×

( ) 1 2

max

xy 1 2 1 2max

don' t confuse withMaximumShear stress2

in strain and that is the difference.2 2 2

σ στ

γ ε ε σ στ

−=

− −= =

IES-36. Ans. (d)

( )− − −∈ − ∈ φ= ⇒ φ = ∈ − ∈ = × − − × = ×x y xy 6 6 6

xy x y 1000 10 600 10 1600 102 2

IES-37. Ans. (c) Three strain gauges are needed on a plane surface to determine the principal strains and their directions.

IES-38. Ans. (b) 1 2 2 11 2and

E E E Eσ σ σ σ

ε μ ε μ= − = − From these two equation eliminate 2σ .

IES-39. Ans. (a) IES-40. Ans. (a)

IAS

IAS-1. Ans. (b) 2nWeknow cos and sin cosσ σ θ τ σ θ θ= =

2100 cos 45 or 200

200sin 45cos 45 100σ σ

τ= =

= =


Chapter-2 Principal Stress and Strain S K Mondal’s IAS-2. Ans. (c)

IAS-3. Ans. (b) It is a case of pure shear so principal planes will be along the diagonal. IAS-4. Ans. (d) Stress in x direction = σx

Therefore x x x, ,x y zE E Eσ σ σε ε μ ε μ= = − = −

IAS-5. Ans. (c)

and 2

ε ε εγ

ε ε ε εε ε ε

⎡ ⎤⎢ ⎥

=⎢ ⎥⎢ ⎥⎣ ⎦

xx xy xzxy

yx yy yz xy

zx zy zz

( )3100 10 0.004 2 MPa 800MPaτ γ= = × × × =xy xyG

IAS-6. Ans. (d) 1 2 1 1max 1

( )2 2

σ σ σ στ σ− − −= = =

IAS-7. Ans. (a) 1 2max 2

σ στ −= Maximum normal stress will developed if 1 2σ σ σ= − =

IAS-8. Ans. (c) 22

max 2 xyyx τ

σστ +⎟⎟

⎠

⎞⎜⎜⎝

⎛ −= = 2

2

302

4040 +⎟⎠⎞

⎜⎝⎛ −−

= 50 MPa

IAS-9. Ans. (c) σb=100MPa τ =20 mPa

σ1,2=2

2

2 2b bσ σ τ⎛ ⎞+ +⎜ ⎟

⎝ ⎠

( )2 2

2 21,2

100 100 20 50 2900 MPa2 2 2 2

σ σσ τ⎛ ⎞ ⎛ ⎞= + + = + + = +⎜ ⎟⎜ ⎟⎝ ⎠⎝ ⎠

b b

IAS-10. Ans. (a) cos 22 2

x y x yn

σ σ σ σσ θ

+ −= +

[We may consider this as 0xyτ = ] ( )x y sayσ σ σ= = So for any planenσ σ= IAS-11. Ans. (d) They are same. IAS-12. Ans. (b)

400 300 400 300cos 2 cos 2 45 350

2 2 2 2x y x y o

n MPaσ σ σ σ

σ θ+ −⎛ ⎞ ⎛ ⎞ + −= + = + × =⎜ ⎟ ⎜ ⎟

⎝ ⎠ ⎝ ⎠

IAS-13. Ans. (a)

σ σ σσ σ σ σ σ σμ μ μ⎛ ⎞ ⎛ ⎞⎛ ⎞∈ = − + ∈ = − + ∈ = − +⎜ ⎟ ⎜ ⎟⎜ ⎟

⎝ ⎠⎝ ⎠ ⎝ ⎠

y y yx z z x z xx y z, and

E E E E E E E E E



( )

( ) ( )

σ σ σ μ σ σ σ

σ σ σμ −

+ +∈ =∈ + ∈ + ∈ = − + +

+ +⎛ ⎞ + −⎛ ⎞= − = − × = ×⎜ ⎟ ⎜ ⎟⎝ ⎠⎝ ⎠

x y zv x y z x y z

x y z 55

2E E

60 20 501 2 1 2 0.35 9 10E 10

IAS-14. Ans. (d) IAS-15. Ans. (b) IAS-16. Ans. (d)

IAS-17. Ans. (d) Maximum shear stress is 2

x yf f−

IAS-18. Ans. (d) ( )x y 2 0Centre ,0 ,0 1, 02 2

σ σ+⎛ ⎞ +⎛ ⎞= =⎜ ⎟ ⎜ ⎟⎝ ⎠⎝ ⎠

2 2

x y 2x

2 0radius 0 12 2

σ στ

−⎛ ⎞ −⎛ ⎞= + = + =⎜ ⎟ ⎜ ⎟⎝ ⎠⎝ ⎠

IAS-19. Ans. (c) Mohr’s circle will be a point.

Radius of the Mohr’s circle = 2

x y 2xy xy x y0 and

2σ σ

τ τ σ σ σ−⎛ ⎞

+ ∴ = = =⎜ ⎟⎝ ⎠

IAS-20. Ans. (b) IAS-21. Ans. (b) IAS-22. Ans. (c) R is false. Stress in one plane always induce a lateral strain with its orthogonal plane.


Conventional Question IES-1999 Question: What are principal in planes? Answer: The planes which pass through the point in such a manner that the resultant stress across

them is totally a normal stress are known as principal planes. No shear stress exists at the principal planes.

Conventional Question IES-2009 Q. The Mohr’s circle for a plane stress is a circle of radius R with its origin at + 2R on σ

axis. Sketch the Mohr’s circle and determine , for this

situation. [2 Marks] Ans. Here

max,σ min ,σ avσ ( )xy maxτ

max 3Rσ =

min

v

max minxy

R3R R 2R

23R Rand R

2 2

σ

σ =+σ = =

σ − σ −τ = = =



Conventional Question IES-1999 Question: Direct tensile stresses of 120 MPa and 70 MPa act on a body on mutually

perpendicular planes. What is the magnitude of shearing stress that can be applied so that the major principal stress at the point does not exceed 135 MPa? Determine the value of minor principal stress and the maximum shear stress.

Answer: Let shearing stress is ' ' MPa.τ

σ

22

1,2

The principal stresses are

120 70 120 702 2

τ⎛ ⎞+ − ⎟⎜= ± +⎟⎜ ⎟⎜⎝ ⎠

σ2

21

Major principal stress is

120 70 120 702 2

135(Given) , 31.2 .or MPa

τ

τ

⎛ ⎞+ − ⎟⎜= + +⎟⎜ ⎟⎜⎝ ⎠

= =

σ2

22

1 2max

Minor principal stress is

120 70 120 70 31.2 55MPa2 2

135 55 40MPa2 2

+ −⎛ ⎞= − + =⎜ ⎟⎝ ⎠

− −= = =σ στ

Conventional Question IES-2009

Q. The state of stress at a point in a loaded machine member is given by the principle stresses. [ 2 Marks]

and . (i) What is the magnitude of the maximum shear stress? (ii) What is the inclination of the plane on which the maximum shear stress acts

with respect to the plane on which the maximum principle stress acts? Ans. (i) Maximum shear stress,

(ii) At θ = 45º max. shear stress occurs with 1σ plane. Since 1σ and 3σ are principle stress does not contains shear stress. Hence max. shear stress is at 45º with principle plane.


R

(2R,0)

R

3R

1 600 MPa,σ = 2 0σ = 3 600 MPaσ = −

1σ

( )1 3 600 6002 2

600 MPa

− −σ − στ = =

=


Chapter-2 Principal Stress and Strain S K Mondal’s Question: A prismatic bar in compression has a cross- sectional area A = 900 mm2 and carries

an axial load P = 90 kN. What are the stresses acts on (i) A plane transverse to the loading axis; (ii) A plane at θ= 60o to the loading axis? Answer: (i) From figure it is clear A plane

transverse to loading axis, θ=0o

2 2n

2

90000cos θ= /900

100 /P 90000 = 2θ= sinθ=0

2A 2×900

σ

τ

∴ =

=

×

P N mmA

N mm

and Sin

(iii) A plane at 60o to loading axis, θ = 90°- 60° = 30°

2 2

n

2

90000cos θ= cos 30900

75 /

PA

N mm

σ = ×

=

2

90000sin2 sin2 602 2 90043.3 /

oPA

N mm

τ θ= = ××

=

Conventional Question IES-2001 Question: A tension member with a cross-sectional area of 30 mm2 resists a load of 80 kN,

Calculate the normal and shear stresses on the plane of maximum shear stress.

Answer: σ θ θ2cos sin22n

P PA A

τ= =

( )

oFor maximum shear stress sin2θ = 1, or, θ = 45

σ33

2max

80 1080 10 cos 45 1333 and 133330 2 30 2n

PMPa MPaA

τ××

= × = = = =×

Conventional Question IES-2007 Question: At a point in a loaded structure, a pure shear stress state τ = ± 400 MPa prevails

on two given planes at right angles. (i) What would be the state of stress across the planes of an element taken at +45°

to the given planes? (ii) What are the magnitudes of these stresses? Answer: (i) For pure shear

maxσ σ ; σ 400τ=− =± =±x y x MPa



(ii) Magnitude of these stresses

σ θ θ2 90 400 and ( cos2 ) 0on xy xy xy xySin Sin MPaτ τ τ τ τ= = = = = − =

Conventional Question IAS-1997 Question: Draw Mohr's circle for a 2-dimensional stress field subjected to (a) Pure shear (b) Pure biaxial tension (c) Pure uniaxial tension and (d) Pure

uniaxial compression Answer: Mohr's circles for 2-dimensional stress field subjected to pure shear, pure biaxial tension, pure

uniaxial compression and pure uniaxial tension are shown in figure below:

Conventional Question IES-2003 Question: A Solid phosphor bronze shaft 60 mm in diameter is rotating at 800 rpm and

transmitting power. It is subjected torsion only. An electrical resistance strain gauge mounted on the surface of the shaft with its axis at 45° to the shaft axis, gives the strain reading as 3.98 × 10–4. If the modulus of elasticity for bronze is 105 GN/m2

and Poisson's ratio is 0.3, find the power being transmitted by the shaft. Bending effect may be neglected.

Answer:

Let us assume maximum shear stress on the cross-sectional plane MU is τ . Then



2

2

1Principal stress along, VM = - 4 = - (compressive)2

1Principal stress along, LU = 4 (tensile)2

τ τ

τ τ=

( )( )

µ 4

4 9

Thus magntude of the compressive strain along VM is

= (1 ) 3.98 10E

3.98 10 105 10= 32.15

1 0.3or MPa

τ

τ

−

−

+ = ×

× × ×=

+

( )

π

π

3

6 3

Torque being transmitted (T) = 16

32.15 10 0.06 =1363.5 Nm16

dτ∴ × ×

= × × ×

π π2 N 2 ×800Power being transmitted, P =T. =T. =1363.5× 114.2360 60

W kWω⎛ ⎞ ⎛ ⎞⎟ ⎟⎜ ⎜∴ =⎟ ⎟⎜ ⎜⎟ ⎟⎜ ⎜⎝ ⎠ ⎝ ⎠

Conventional Question IES-2002 Question: The magnitude of normal stress on two mutually perpendicular planes, at a point in

an elastic body are 60 MPa (compressive) and 80 MPa (tensile) respectively. Find the magnitudes of shearing stresses on these planes if the magnitude of one of the principal stresses is 100 MPa (tensile). Find also the magnitude of the other principal stress at this point.

Answer: Above figure shows stress condition assuming shear stress is ' τ xy'

Principal stresses

2

y 21,2

σ σ σ σσ

2 2τ

⎛ ⎞+ − ⎟⎜ ⎟= ± +⎜ ⎟⎜ ⎟⎜⎝ ⎠x y x

xy

2

21,2

60 80 60 80,σ2 2

τ⎛ ⎞− + − − ⎟⎜= ± +⎟⎜ ⎟⎜⎝ ⎠ xyor

2

21,2

60 80 60 80,σ2 2

τ⎛ ⎞− + − − ⎟⎜= ± +⎟⎜ ⎟⎜⎝ ⎠ xyor

80Mpa

80Mpa

60Mpa60Mpa

Jxy

Jxy

Jxy

Jxy

2 21

To make principal stress 100 MPa we have to consider '+' .

σ 100 MPa 10 70 ; or, 56.57 MPaτ τ∴ = = + + =xy xy

2

22

Therefore other principal stress will be

60 80 60 80σ (56.57)2 2

. . 80MPa(compressive)i e

⎛ ⎞− + − − ⎟⎜= − +⎟⎜ ⎟⎜⎝ ⎠

Conventional Question IES-2001 Question: A steel tube of inner diameter 100 mm and wall thickness 5 mm is subjected to a

torsional moment of 1000 Nm. Calculate the principal stresses and orientations of the principal planes on the outer surface of the tube.

Answer: ( ) ( )π 4 4 6 4Polar moment of Inertia (J)= 0.110 0.100 = 4.56 1032

m−⎡ ⎤− ×⎢ ⎥⎣ ⎦



6

T . 1000 (0.055)Now 4.56 10

12.07MPa

T Ror JJ R J

τ−

×= = =

×

=

pθ σ σ

θ

σ θ

σ

0 0p

01

02

2Now,tan2 ,

gives 45 135

2 12.07 sin9012.07

12.07sin27012.07

xy

x y

xy

or

Sin

MPaand

MPa

τ

τ

= =∝−

=

∴ = = ×

=

=

=−

50mm

5mm

Conventional Question IES-2000 Question: At a point in a two dimensional stress system the normal stresses on two mutually

perpendicular planes are yand σ σx and the shear stress is τ xy. At what value of shear stress, one of the principal stresses will become zero?

Answer: Two principal stressdes are

2

21,2

σ σ σ -σσ

2 2τ

⎛ ⎞+ ⎟⎜ ⎟= ± +⎜ ⎟⎜ ⎟⎜⎝ ⎠x y x y

xy

Considering (-)ive sign it may be zero

2 2 2

xx 2 2σ σ σ σ σ σσ σor,

2 2 22τ τ

⎛ ⎞ ⎛ ⎞ ⎛ ⎞⎛ ⎞ − + −+ ⎟ ⎟ ⎟⎟ ⎜ ⎜ ⎜⎜ ⎟ ⎟ ⎟∴ = + = +⎟ ⎜ ⎜ ⎜⎜ ⎟ ⎟ ⎟⎟ ⎜ ⎜ ⎜⎜ ⎟ ⎟ ⎟⎟ ⎜ ⎜ ⎜⎜ ⎝ ⎠ ⎝ ⎠ ⎝ ⎠⎝ ⎠x y y x yy

xy xy

2 2

2 2y

σ σ σ σor, or, σ σ or, σ σ

2 2τ τ τ

⎛ ⎞ ⎛ ⎞+ −⎟ ⎟⎜ ⎜= ⎟ − ⎟ = =±⎜ ⎜⎟ ⎟⎜ ⎜⎟ ⎟⎝ ⎠ ⎝ ⎠x y x y

xy xy x y xy x

Conventional Question IES-1996 Question: A solid shaft of diameter 30 mm is fixed at one end. It is subject to a tensile force of

10 kN and a torque of 60 Nm. At a point on the surface of the shaft, determine the principle stresses and the maximum shear stress.

Answer: Given: D = 30 mm = 0.03 m; P = 10 kN; T= 60 Nm

( ) ( )1 2 max

36 2 2

t x2

Pr incipal stresses , and max imum shear stress :

10 10Tensile stress 14.15 10 N / m or 14.15 MN / m0.03

4

σ σ τ

σ σ π×= = = ×

×

TAs per torsion equation,J R

τ=



( )6 2

44

2

TR TR 60 0.015Shear stress, 11.32 10 N / mJ D 0.03

32 32or 11.32 MN / m

τ π π×∴ = = = = ×

×

( )

2x y x y 2

1 2 xy

2 2x y xy

22

1 2

2

The principal stresses are calculated by using the relations :

,2 2

Here 14.15MN / m , 0; 11.32 MN / m

14.15 14.15, 11.322 2

7.07 13.35 20.425 MN / m , 6.275M

σ σ σ σσ τ

σ σ τ τ

σ

⎡ ⎤+ −⎛ ⎞ ⎛ ⎞⎢ ⎥= ± +⎜ ⎟ ⎜ ⎟⎢ ⎥⎝ ⎠ ⎝ ⎠⎣ ⎦

= = = =

⎛ ⎞∴ = ± +⎜ ⎟⎝ ⎠

= ± = −

( )( )

( )

2

21

22

21 2max

N / m .Hence,major principal stress, 20.425 MN / m tensile

Minor principal stress, 6.275MN / m compressive

24.425 6.275Maximum shear stress, 13.35mm / m

2 2

σ

σ

σ στ

=

=

− −−= = =

Conventional Question IES-2000 Question: Two planes AB and BC which are at right angles are acted upon by tensile stress of

140 N/mm2 and a compressive stress of 70 N/mm2 respectively and also by shear stress 35 N/mm2. Determine the principal stresses and principal planes. Find also the maximum shear stress and planes on which they act.

Sketch the Mohr circle and mark the relevant data. Answer: Given

x

y

σ =140MPa(tensile)σ =-70MPa(compressive)

35MPaxyτ =

σ σ1 2Principal stresses; , ;

70N/mm2

35Nmm2

A

C B

140N/mm2

xσ σ σ σσ

σ σ

22

1,2

22

1 2

We know that, 2 2

140 70 140 70 35 35 110.72 2

Therefore =145.7 MPa and 75.7MPa

x y yxyτ

⎛ ⎞+ − ⎟⎜ ⎟= ± +⎜ ⎟⎜ ⎟⎜⎝ ⎠

⎛ ⎞− + ⎟⎜= ± + = ±⎟⎜ ⎟⎜⎝ ⎠

=−

y

θ θ

θσ σ

σ - σ

1 2

1 2max

Position of Principal planes ,2 2 35tan2 0.3333

140 70

145 75.7Maximum shear stress, 110.72 2

xyp

x

MPa

τ

τ

×= = =

− +

+= = =


Chapter-2 Principal Stress and Strain S K Mondal’s Mohr cirle:

σσ

xOL= 14070

35

Joining ST that cuts at 'N'

y

xy

MPaOM MPa

SM LT MPaτ

=

= =−

= = =

σσ

1

2

SN=NT=radius of Mohr circle =110.7 MPaOV= 145.7

75.7MPa

OV MPa=

= =−

T

VL

2 =198.4θpS

UM O 2θ=78.4

σ 140=

Y

N

Conventional Question IES-2010 Q6. The data obtained from a rectangular strain gauge rosette attached to a stressed

steel member are 6 6 60 45 90220 10 , 120 10 220 10andε ε ε− − −= − × = × = × . Given that the

value of E = and Poisson’s Ratio , calculate the values of principal stresses acting at the point and their directions. [10 Marks]

Ans. Use rectangular strain gauge rosette Conventional Question IES-1998 Question: When using strain-gauge system for stress/force/displacement measurements how

are in-built magnification and temperature compensation achieved? Answer: In-built magnification and temperature compensation are achieved by (a) Through use of adjacent arm balancing of Wheat-stone bridge. (b) By means of self temperature compensation by selected melt-gauge and dual element-

gauge. Conventional Question AMIE-1998 Question: A cylinder (500 mm internal diameter and 20 mm wall thickness) with closed ends is

subjected simultaneously to an internal pressure of 0-60 MPa, bending moment 64000 Nm and torque 16000 Nm. Determine the maximum tensile stress and shearing stress in the wall.

Answer: Given: d = 500 mm = 0·5 m; t = 20 mm = 0·02 m; p = 0·60 MPa = 0.6 MN/m2; M = 64000 Nm = 0·064 MNm; T= 16000 Nm = 0·016 MNm. Maximum tensile stress: First let us determine the principle stresses 1 2andσ σ assuming this as a thin cylinder.

We know, 21

pd 0.6 0.5 7.5MN / m2t 2 0.02

σ ×= = =×

22

pd 0.6 0.5and 3.75MN / m4t 4 0.02

σ ×= = =×

Next consider effect of combined bending moment and torque on the walls of the cylinder. Then the principal stresses 1 2' and 'σ σ are given by

5 22 10 N / mm× 0.3μ =



( )

( )

2 21 3

2 22 3

2 2 21 3

2 2 22 3

max

I IImax

II 2 2

16' M M Td

16and ' M M Td16' 0.064 0.064 0.016 5.29MN / m0.516and ' 0.064 0.064 0.016 0.08MN / m0.5

Maximum shearing stress, :

We Know,2

' 3.75

σπ

σπ

σπ

σπ

τσ στ

σ σ σ

⎡ ⎤= + +⎣ ⎦

⎡ ⎤= − +⎣ ⎦

⎡ ⎤∴ = + + =⎣ ⎦×

⎡ ⎤= − + = −⎣ ⎦×

−=

= + = − ( )2

2max

0.08 3.67MN / m tensile12.79 3.67 4.56MN / m

2τ

=

−∴ = =


3. Moment of Inertia and Centroid

Theory at a Glance (for IES, GATE, PSU) 3.1 Centre of gravity

The centre of gravity of a body defined as the point through which the whole weight of a body may be

assumed to act.

3.2 Centroid or Centre of area

The centroid or centre of area is defined as the point where the whole area of the figure is assumed to be

concentrated.

3.3 Moment of Inertia (MOI)

• About any point the product of the force and the perpendicular distance between them is known as

moment of a force or first moment of force.

• This first moment is again multiplied by the perpendicular distance between them to obtain second

moment of force.

• In the same way if we consider the area of the figure it is called second moment of area or area

moment of inertia and if we consider the mass of a body it is called second moment of mass or mass

moment of Inertia.

• Mass moment of inertia is the measure of resistance of the body to rotation and forms the basis

of dynamics of rigid bodies.

• Area moment of Inertia is the measure of resistance to bending and forms the basis of strength

of materials.

3.4 Mass moment of Inertia (MOI)

2i i

iI m r= ∑

• Notice that the moment of inertia ‘I’ depends on the distribution of mass in the system.

• The furthest the mass is from the rotation axis, the bigger the moment of inertia.

• For a given object, the moment of inertia depends on where we choose the rotation axis.

• In rotational dynamics, the moment of inertia ‘I’ appears in the same way that mass m does in

linear dynamics.


Chapter-3 Moment of Inertia and Centroid • Solid disc or cylinder of mass M and radius R, about perpendicular axis through its centre,

212

I MR=

• Solid sphere of mass M and radius R, about an axis through its centre, I = 2/5 M R2

• Thin rod of mass M and length L, about a perpendicular axis through

its centre.

2112

I ML=

• Thin rod of mass M and length L, about a perpendicular axis through its

end.

21

3I ML=

3.5 Area Moment of Inertia (MOI) or Second moment of area

• To find the centroid of an area by the first moment of the area

about an axis was determined ( ∫ x dA )

• Integral of the second moment of area is called moment of

inertia (∫ x2dA)

• Consider the area ( A )

• By definition, the moment of inertia of the differential area

about the x and y axes are dIxx and dIyy

• dIxx = y2dA Ixx = ∫ y2 dA

• dIyy = x2dA Iyy = ∫ x2 dA

3.6 Parallel axis theorem for an areaThe rotational inertia about any axis is the sum of

second moment of inertia about a parallel axis

through the C.G and total area of the body times

square of the distance between the axes.

INN = ICG + Ah2


Chapter-3 Moment of Inertia and Centroid 3.7 Perpendicular axis theorem for an areaIf x, y & z are mutually perpendicular axes as shown, then

( )zz xx yyI J I I= +

Z-axis is perpendicular to the plane of x – y and vertical to this page as

shown in figure.

• To find the moment of inertia of the differential area about the pole (point of origin) or z-axis, (r) is used. (r) is the perpendicular distance from the pole to dA for the entire area

J = ∫ r2 dA = ∫ (x2 + y2 )dA = Ixx + Iyy (since r2 = x2 + y2 )

Where, J = polar moment of inertia

3.8 Moments of Inertia (area) of some common area (i) MOI of Rectangular area

Moment of inertia about axis XX which passes

through centroid.

Take an element of width ‘dy’ at a distance y

from XX axis.

∴ Area of the element (dA) = b× dy.

and Moment of Inertia of the element about XX

axis 2 2dA y b.y .dy= × =

∴Total MOI about XX axis (Note it is area

moment of Inertia)

32 2

2 2

02

212

h h

xxh

bhI by dy by dy+

−

= = =∫ ∫

3

12xx

bhI =

Similarly, we may find, 3

12yyhbI =

∴Polar moment of inertia (J) = Ixx + Iyy = 3 3

12 12bh hb

+


Chapter-3 Moment of Inertia and Centroid If we want to know the MOI about an axis NN passing

through the bottom edge or top edge.

Axis XX and NN are parallel and at a distance h/2.

Therefore INN = Ixx + Area × (distance) 2

23 3

12 2 3bh h bhb h ⎛ ⎞= + × × =⎜ ⎟

⎝ ⎠

Case-I: Square area

4

12xxaI =

Case-II: Square area with diagonal as axis

4

12xxaI =

Case-III: Rectangular area with a centrally

rectangular hole Moment of inertia of the area = moment of inertia of BIG

rectangle – moment of inertia of SMALL rectangle

3 3

12 12xxBH bhI = −


Chapter-3 Moment of Inertia and Centroid (ii) MOI of a Circular area The moment of inertia about axis XX this passes through

the centroid. It is very easy to find polar moment of inertia about point ‘O’. Take an element of width ‘dr’ at a distance ‘r’ from centre. Therefore, the moment of inertia of this

element about polar axis 2

xx yy2

d(J) = d(I + I ) = area of ring (radius)or d(J) 2 rdr rπ

×

= ×

4 43

0

4

Integrating both side we get

22 32

Due to summetry

Therefore, 2 64

R

xx yy

xx yy

R DJ r dr

I IJ DI I

π ππ

π

= = =

=

= = =

∫

4 4

and 64 32xx yyD DI I Jπ π

= = =

Case-I: Moment of inertia of a circular

area with a concentric hole. Moment of inertia of the area = moment of inertia of BIG circle – moment of inertia of SMALL circle.

Ixx = Iyy = 4

64Dπ –

4

64dπ

4 4

4 4

( )64

and ( )32

D d

J D d

π

π

= −

= −

Case-II: Moment of inertia of a semi-circular area.

4 4

1 of the momemt of total circular lamina21 2 64 128

NNI

D Dπ π

=

⎛ ⎞= × =⎜ ⎟

⎝ ⎠

We know that distance of CG from base is

( )4 2D h say3 3

rπ π

= =

i.e. distance of parallel axis XX and NN is (h) ∴According to parallel axis theory


Chapter-3 Moment of Inertia and Centroid

( )

( )

2

4 22

4 2

Area × distance1or

128 2 41 2or

128 2 4 3

NN G

xx

xx

I ID DI h

D D DI

π π

π ππ

= +

⎛ ⎞= + ×⎜ ⎟

⎝ ⎠⎛ ⎞ ⎛ ⎞= + × ×⎜ ⎟ ⎜ ⎟

⎝ ⎠⎝ ⎠

or 40.11xxI R=

Case – III: Quarter circle area IXX = one half of the moment of Inertia of the Semi-circular area about XX.

( )4 41 0.11 0.055 2XXI R R= × =

40.055XXI R=

INN = one half of the moment of Inertia of the Semi-circular area about NN.

4 412 64 128NN

D DI π π∴ = × =

(iii) Moment of Inertia of a Triangular area

(a) Moment of Inertia of a Triangular area of

a axis XX parallel to base and passes through

C.G.

3

36XXbhI =

(b) Moment of inertia of a triangle about an

axis passes through base

3

12NNbhI =


Chapter-3 Moment of Inertia and Centroid (iv) Moment of inertia of a thin circular ring: Polar moment of Inertia

( ) 2J R area of whole ring= ×

2 3R 2 Rt 2 R tπ π= × =

3 2XX YYJI I R tπ= = =

(v) Moment of inertia of a elliptical area

3

4XXabI π=

Let us take an example: An I-section beam of 100 mm wide, 150 mm depth flange and web of thickness 20 mm is used in a structure of length 5 m. Determine the Moment of Inertia (of area) of cross-section of the beam. Answer: Carefully observe the figure below. It has sections with symmetry about the neutral axis.

We may use standard value for a rectangle about an axis passes through centroid. i.e.

3

.12bhI = The

section can thus be divided into convenient rectangles for each of which the neutral axis passes the

centroid. ( )Re tan

3 34

-4 4

-

0.100 0.150 0.40 0.130-2 m12 12

1.183 10 m

Beam c gle Shaded areaI I I=

⎡ ⎤× ×⎢ ⎥= ×⎢ ⎥⎣ ⎦

= ×

3.9 Radius of gyration Consider area A with moment of inertia Ixx. Imagine

that the area is concentrated in a thin strip parallel to

the x axis with equivalent Ixx.



2xx xxI k A= or

xxxx

IkA

=

kxx =radius of gyration with respect to the x axis.

Similarly

2yy yyI k A= or

yyyy

Ik

A=

2oJ k A= or o

JkA

=

2 2 2o xx yyk k k= +

Let us take an example: Find radius of gyration for a circular area of diameter ‘d’ about central axis.

Answer:

We know that, 2xx xxI K A=



or

4

264

44

XXXX

dI dKA d

π

π= = =





Moment of Inertia (Second moment of an area) GATE-1. The second moment of a circular area about the diameter is given by (D is the

diameter) [GATE-2003]

(a) 4

4Dπ (b)

4

16Dπ (c)

4

32Dπ (d)

4

64Dπ

GATE-2. The area moment of inertia of a square of size 1 unit about its diagonal is: [GATE-2001]

(a) 13

(b) 14

(c) 112

(d) 16

Radius of Gyration Data for Q3–Q4 are given below. Solve the problems and choose correct

answers.

A reel of mass “m” and radius of gyration “k” is rolling down smoothly from rest with one end of the thread wound on it held in the ceiling as depicted in the figure. Consider the thickness of

the thread and its mass negligible in comparison with the radius “r” of the hub and the reel

mass “m”. Symbol “g” represents the acceleration due to gravity. [GATE-2003]

GATE-3. The linear acceleration of the reel is:

(a) ( )

2

2 2

grr k+

(b) ( )

2

2 2

gkr k+

(c) ( )2 2

grkr k+

(d) ( )

2

2 2

mgrr k+

GATE-4. The tension in the thread is:

(a) ( )2

2 2

mgrr k+

(b) ( )2 2

mgrkr k+

(c) ( )2

2 2

mgkr k+

(d) ( )2 2

mgr k+

GATE-5. For the section shown below, second moment of the area about an axis 4d distance

above the bottom of the area is [CE: GATE-2006]



b

d

(a) 3

48bd (b)

3

12bd (c)

3748bd (d)

3

3bd

GATE-6. A disc of radius r has a hold of radius 2r cut-out as shown. The centroid of the

remaining disc(shaded portion) at a radial distance from the centre “O” is

O O′

r/2

[CE: GATE-2010]

(a) 2r (b)

3r (c)

6r (d)

8r


Centroid IES-1. Assertion (A): Inertia force always acts through the centroid of the body and is

directed opposite to the acceleration of the centroid. [IES-2001] Reason (R): It has always a tendency to retard the motion. (a) Both A and R are individually true and R is the correct explanation of A (b) Both A and R are individually true but R is NOT the correct explanation of A (c) A is true but R is false (d) A is false but R is true

Radius of Gyration IES-2. Figure shows a rigid body of mass

m having radius of gyration k about its centre of gravity. It is to be replaced by an equivalent dynamical system of two masses placed at A and B. The mass at A should be:

(a) a ma b

×+

(b) b ma b

×+

(c) 3m a

b× (d)

2m b

a×

[IES-2003] IES-3. Force required to accelerate a cylindrical body which rolls without slipping on a

horizontal plane (mass of cylindrical body is m, radius of the cylindrical surface in


Chapter-3 Moment of Inertia and Centroid contact with plane is r, radius of gyration of body is k and acceleration of the body is a) is: [IES-2001]

(a) ( )2 2/ 1 .m k r a+ (b) ( )2 2/ .mk r a (c) 2.mk a (d) ( )2 / 1 .mk r a+ IES-4. A body of mass m and radius of gyration k is to be replaced by two masses m1 and m2

located at distances h1 and h2 from the CG of the original body. An equivalent dynamic system will result, if [IES-2001]

(a) 1 2h h k+ = (b) 2 2 21 2h h k+ = (c) 2

1 2h h k= (d) 21 2h h k=


Radius of Gyration IAS-1. A wheel of centroidal radius of gyration 'k' is rolling on a horizontal surface with

constant velocity. It comes across an obstruction of height 'h' Because of its rolling speed, it just overcomes the obstruction. To determine v, one should use the principle (s) of conservation of [IAS 1994]

(a) Energy (b) Linear momentum (c) Energy and linear momentum (d) Energy and angular momentum

OBJECTIVE ANSWERS

GATE-1. Ans. (d)

GATE-2. Ans. (c) ( )44 112 12xxaI = =

GATE-3. Ans. (a) For downward linear motion mg – T = mf, where f = linear tangential acceleration = rα,

α = rotational acceleration. Considering rotational motion .Tr Iα=

or, T = 22fmkr

× therefore mg – T = mf gives f = ( )2

2 2

grr k+



GATE-4. Ans. (c) ( ) ( )2 2

2 22 2 2 2 2 2

f gr mgkT mk mkr r r k r k

= × = × =+ +

GATE-5. Ans. (c) Using parallel axis theorem, we get the second moment of inertia as

⎛ ⎞= + − = + =⎜ ⎟⎝ ⎠

23 3 3 37I12 2 4 12 16 48bd d d bd bd bdbx

GATE-6. Ans. (c) The centroid of the shaded portion of the disc is given by

+=

+1 1 2 2

1 2

A AA Ax xx

where x is the radial distance from Q. = π 2

1A ;r =1 0;x

π⎛ ⎞= − π × = −⎜ ⎟⎝ ⎠

2 2

2A2 4r r

=2 2rx

∴

π ππ × − ×= = −

π ππ −

2 22

2 22

04 2 2

34

r r rrx

r rr

⇒ = −6rx

IES-1. Ans. (c) It has always a tendency to oppose the motion not retard. If we want to retard a motion then it will wand to accelerate.

IES-2. Ans. (b) IES-3. Ans. (a) IES-4. Ans. (c) IAS-1. Ans. (a)


Conventional Question IES-2004 Question: When are I-sections preferred in engineering applications? Elaborate your answer. Answer: I-section has large section modulus. It will reduce the stresses induced in the material. Since

I-section has the considerable area are far away from the natural so its section modulus increased.


4. Bending Moment and Shear Force

Diagram

Theory at a Glance (for IES, GATE, PSU) 4.1 Shear Force and Bending Moment

At first we try to understand what shear force is and what is bending moment?

We will not introduce any other co-ordinate system.

We use general co-ordinate axis as shown in the

figure. This system will be followed in shear force and

bending moment diagram and in deflection of beam.

Here downward direction will be negative i.e.

negative Y-axis. Therefore downward deflection of the

beam will be treated as negative.

We use above Co-ordinate system

Some books fix a co-ordinate axis as shown in the

following figure. Here downward direction will be

positive i.e. positive Y-axis. Therefore downward

deflection of the beam will be treated as positive. As beam is generally deflected in downward directions

and this co-ordinate system treats downward

deflection is positive deflection.

Some books use above co-ordinate system

Consider a cantilever beam as shown subjected to external load ‘P’. If we imagine this beam to be cut by a section X-X, we see that the applied force tend to displace the left-hand portion of the beam relative to the right hand portion, which is fixed in the wall. This tendency is resisted by internal forces between the two parts of the beam. At the cut section a resistance shear force (Vx) and a bending moment (Mx) is induced. This resistance shear force and the bending moment at the cut section is shown in the left hand and right hand portion of the cut beam. Using the three equations of equilibrium

0 , 0 0x y iF F and M= = =∑ ∑ ∑

We find that xV P= − and .xM P x= −

In this chapter we want to show pictorially the


Chapter-4 Bending Moment and Shear Force Diagram S K Mondal’s variation of shear force and bending moment in a

beam as a function of ‘x' measured from one end of

the beam.

Shear Force (V) ≡ equal in magnitude but opposite in direction

to the algebraic sum (resultant) of the components in the

direction perpendicular to the axis of the beam of all external

loads and support reactions acting on either side of the section being considered.

Bending Moment (M) equal in magnitude but opposite in

direction to the algebraic sum of the moments about (the

centroid of the cross section of the beam) the section of all

external loads and support reactions acting on either side of the section being considered.

What are the benefits of drawing shear force and bending moment diagram?

The benefits of drawing a variation of shear force and bending moment in a beam as a function of ‘x'

measured from one end of the beam is that it becomes easier to determine the maximum absolute value of

shear force and bending moment. The shear force and bending moment diagram gives a clear picture in our mind about the variation of SF and BM throughout the entire section of the beam.

Further, the determination of value of bending moment as a function of ‘x' becomes very important so as to

determine the value of deflection of beam subjected to a given loading where we will use the formula, 2

2 xd yEI Mdx

= .

4.2 Notation and sign convention

• Shear force (V) Positive Shear Force

A shearing force having a downward direction to the right hand side of a section or upwards to the

left hand of the section will be taken as ‘positive’. It is the usual sign conventions to be followed for

the shear force. In some book followed totally opposite sign convention.


Chapter-4 Bending Moment and Shear Force Diagram S K Mondal’s

The upward direction shearing

force which is on the left hand

of the section XX is positive

shear force.

The downward direction

shearing force which is on the

right hand of the section XX is

positive shear force.

Negative Shear Force

A shearing force having an upward direction to the right hand side of a section or downwards to the

left hand of the section will be taken as ‘negative’.

The downward direction

shearing force which is on the

left hand of the section XX is

negative shear force.

The upward direction shearing

force which is on the right

hand of the section XX is

negative shear force.

• Bending Moment (M) Positive Bending Moment

A bending moment causing concavity upwards will be taken as ‘positive’ and called as sagging

bending moment.



Sagging

If the bending moment of the left hand of the section

XX is clockwise then it is a

positive bending moment.

If the bending moment of the right hand of the

section XX is anti-

clockwise then it is a positive bending moment.

A bending moment causing concavity upwards will be

taken as ‘positive’ and

called as sagging bending

moment.

Negative Bending Moment

Hogging

If the bending moment of

the left hand of the section

XX is anti-clockwise then

it is a positive bending

moment.

If the bending moment of

the right hand of the

section XX is clockwise

then it is a positive

bending moment.

A bending moment causing

convexity upwards will be

taken as ‘negative’ and called as hogging bending moment.

Way to remember sign convention

• Remember in the Cantilever beam both Shear force and BM are negative (–ive).

4.3 Relation between S.F (Vx), B.M. (Mx) & Load (w)

• xdV = -w (load)

dxThe value of the distributed load at any point in the beam is equal to

the slope of the shear force curve. (Note that the sign of this rule may change depending on the sign

convention used for the external distributed load).

• x

xdM = Vdx

The value of the shear force at any point in the beam is equal to the slope of the

bending moment curve.



4.4 Procedure for drawing shear force and bending moment diagram Construction of shear force diagram

• From the loading diagram of the beam constructed shear force diagram.

• First determine the reactions.

• Then the vertical components of forces and reactions are successively summed from the left end of

the beam to preserve the mathematical sign conventions adopted. The shear at a section is simply

equal to the sum of all the vertical forces to the left of the section.

• The shear force curve is continuous unless there is a point force on the beam. The curve then

“jumps” by the magnitude of the point force (+ for upward force).

• When the successive summation process is used, the shear force diagram should end up with the previously calculated shear (reaction at right end of the beam). No shear force acts through the

beam just beyond the last vertical force or reaction. If the shear force diagram closes in this fashion,

then it gives an important check on mathematical calculations. i.e. The shear force will be zero at

each end of the beam unless a point force is applied at the end.

Construction of bending moment diagram

• The bending moment diagram is obtained by proceeding continuously along the length of beam from

the left hand end and summing up the areas of shear force diagrams using proper sign convention.

• The process of obtaining the moment diagram from the shear force diagram by summation is

exactly the same as that for drawing shear force diagram from load diagram.

• The bending moment curve is continuous unless there is a point moment on the beam. The curve

then “jumps” by the magnitude of the point moment (+ for CW moment).

• We know that a constant shear force produces a uniform change in the bending moment, resulting in straight line in the moment diagram. If no shear force exists along a certain portion of a beam,

then it indicates that there is no change in moment takes place. We also know that dM/dx= Vx

therefore, from the fundamental theorem of calculus the maximum or minimum moment occurs

where the shear is zero.

• The bending moment will be zero at each free or pinned end of the beam. If the end is built in, the

moment computed by the summation must be equal to the one calculated initially for the reaction.

4.5 Different types of Loading and their S.F & B.M Diagram (i) A Cantilever beam with a concentrated load ‘P’ at its free end.


Chapter-4 Bending Moment and Shear Force Diagram S K Mondal’s Shear force:

At a section a distance x from free end consider the forces to

the left, then (Vx) = - P (for all values of x) negative in sign

i.e. the shear force to the left of the x-section are in downward

direction and therefore negative.

Bending Moment:

Taking moments about the section gives (obviously to the left

of the section) Mx = -P.x (negative sign means that the

moment on the left hand side of the portion is in the

anticlockwise direction and is therefore taken as negative

according to the sign convention) so that the maximum

bending moment occurs at the fixed end i.e. Mmax = - PL

(at x = L)

S.F and B.M diagram

(ii) A Cantilever beam with uniformly distributed load over the whole length

When a cantilever beam is subjected to a uniformly distributed load whose intensity is given w /unit length. Shear force: Consider any cross-section XX which is at a distance of x from the free end. If we just take the resultant of all the forces on the left of the X-section, then Vx = -w.x for all values of ‘x'. At x = 0, Vx = 0 At x = L, Vx = -wL (i.e. Maximum at fixed end) Plotting the equation Vx = -w.x, we get a straight line because it is a equation of a straight line y (Vx) = m(- w) .x Bending Moment: Bending Moment at XX is obtained by treating the load to the left of XX as a concentrated load of the same value (w.x) acting through the centre of gravity at x/2.

S.F and B.M diagram

Therefore, the bending moment at any cross-section XX is

( )= − = −2.. .

2 2xx w xM w x

Therefore the variation of bending moment is according to parabolic law.

The extreme values of B.M would be

at x = 0, Mx = 0

and x = L, Mx = 2

2wL−



Maximum bending moment, =2

maxwL2

M at fixed end

Another way to describe a cantilever beam with uniformly distributed load (UDL) over it’s whole length.

(iii) A Cantilever beam loaded as shown below draw its S.F and B.M diagram

In the region 0 < x < a

Following the same rule as followed previously, we get

x xV =- P; and M = - P.x

In the region a < x < L

( )x xV =- P+P=0; and M = - P.x +P .x a P a− =

S.F and B.M diagram

(iv) Let us take an example: Consider a cantilever bean of 5 m length. It carries a uniformly distributed

load 3 KN/m and a concentrated load of 7 kN at the free end and 10 kN at 3 meters from the fixed end.

Draw SF and BM diagram.

Answer: In the region 0 < x < 2 m

Consider any cross section XX at a distance x from free end.

Shear force (Vx) = -7- 3x

So, the variation of shear force is linear.

at x = 0, Vx = -7 kN

at x = 2 m , Vx = -7 - 3×2 = -13 kN

at point Z Vx = -7 -3×2-10 = -23 Kn



Bending moment (Mx) = -7x - (3x). 2x 3x 7x

2 2= − −

So, the variation of bending force is parabolic.

at x = 0, Mx = 0

at x = 2 m, Mx = -7×2 – (3×2) × 22

= - 20 kNm

In the region 2 m < x < 5 m

Consider any cross section YY at a distance x from free end Shear force (Vx) = -7 - 3x – 10 = -17- 3x

So, the variation of shear force is linear.

at x = 2 m, Vx = - 23 kN

at x = 5 m, Vx = - 32 kN

Bending moment (Mx) = - 7x – (3x) x2

⎛ ⎞×⎜ ⎟⎝ ⎠

- 10 (x - 2)

23 x 17 202

x= − − +

So, the variation of bending force is parabolic.

at x = 2 m, Mx 23 2 17 2 202

= − × − × + = - 20 kNm

at x = 5 m, Mx = - 102.5 kNm

(v) A Cantilever beam carrying uniformly varying load from zero at free end and w/unit

length at the fixed end



Consider any cross-section XX which is at a distance of x from the free end.

At this point load (wx) = w .xL

Therefore total load (W) L L

x0 0

wLw dx .xdx = L 2w= =∫ ∫

( ) =

⎛ ⎞= − = −⎜ ⎟⎝ ⎠

∴=

−= − =

2

max

area of ABC (load triangle)

1 w wx . x .x2 2L

The shear force variation is parabolic.at x = 0, V 0

WL WLat x = L, V i.e. Maximum Shear force (V ) at fi2 2

x

x

L

xShear force V

xed end

( ) = ×

⎛ ⎞= − = −⎜ ⎟⎝ ⎠

∴=

= − =

2 3

2 2

max

load distance from centroid of triangle ABC

wx x wx.2L 3 6L

The bending moment variation is cubic.at x= 0, M 0

wL wLat x = L, M i.e. Maximum Bending moment (M ) at fix6 6

x

x

xBending moment M

ed end.



( )( )

= − = −

= −

x

Integration method

d V wWe know that load .xdx L

wor d(V ) .x .dxLx

Alternative way :

( )V x

0 02

Integrating both side

wd V . x .dxL

w xor V .L 2

x

x

x

= −

= −

∫ ∫

( )

( )

2x

x

2

x

Again we know thatd M wx V -

dx 2Lwxor d M - dx2L

= =

=

( )x

M 2

x0 0

3 3

x

Integrating both side we get at x=0,M =0

wxd(M ) .dx2L

w x wxor M - × -2L 3 6L

x x

= −

= =

∫ ∫

(vi) A Cantilever beam carrying gradually varying load from zero at fixed end and w/unit

length at the free end

Considering equilibrium we get, ( )2

A AwL wLM and Reaction R3 2

= =

Considering any cross-section XX which is at a distance of x from the fixed end.

At this point load W(W ) .xLx =

Shear force ( ) = −AR area of triangle ANMxV

2

x max

x

wL 1 w wL wx- . .x .x = + - 2 2 L 2 2L

The shear force variation is parabolic.wL wLat x 0, V i.e. Maximum shear force, V2 2

at x L, V 0

⎛ ⎞= ⎜ ⎟⎝ ⎠

∴

= = + = +

= =

Bending moment ( )2

A Awx 2x=R .x - . - M2L 3xM



( )

3 2

2 2

max

x

wL wx wL= .x - - 2 6L 3

The bending moment variation is cubicwL wLat x = 0, M i.e.Maximum B.M. M .3 3

at x L, M 0

x

∴

= − = −

= =

(vii) A Cantilever beam carrying a moment M at free end

Consider any cross-section XX which is at a distance of x from the free end. Shear force: Vx = 0 at any point. Bending moment (Mx) = -M at any point, i.e. Bending moment is constant throughout the length.

(viii) A Simply supported beam with a concentrated load ‘P’ at its mid span.



Considering equilibrium we get, A BPR = R = 2

Now consider any cross-section XX which is at a distance of x from left end A and section YY at a distance from left end A, as shown in figure below.

Shear force: In the region 0 < x < L/2 Vx = RA = + P/2 (it is constant) In the region L/2 < x < L

Vx = RA – P =2P

- P = - P/2 (it is constant)

Bending moment: In the region 0 < x < L/2

Mx = P2

.x (its variation is linear)

at x = 0, Mx = 0 and at x = L/2 Mx =PL4

i.e. maximum

Maximum bending moment, =maxPL4

M at x = L/2 (at mid-point)

In the region L/2 < x < L

Mx =2P

.x – P(x - L/2) =PL2

− P2

.x (its variation is linear)

at x = L/2 , Mx =PL4

and at x = L, Mx = 0

(ix) A Simply supported beam with a concentrated load ‘P’ is not at its mid span.

Considering equilibrium we get, RA = BPb Paand R =L L

Now consider any cross-section XX which is at a distance x from left end A and another section YY at a distance x from end A as shown in figure below.


Chapter-4 Bending Moment and Shear Force Diagram S K Mondal’s Shear force: In the range 0 < x < a

Vx = RA = +PbL

(it is constant)

In the range a < x < L

Vx = RA - P = -PaL

(it is constant)

Bending moment: In the range 0 < x < a

Mx = +RA.x = PbL

.x (it is variation is linear)

at x = 0, Mx = 0 and at x = a, Mx =Pab

L (i.e. maximum)

In the range a < x < L

Mx = RA.x – P(x- a) =PbL

.x – P.x + Pa (Put b = L - a)

= Pa (1 - x1L

Pa ⎛ ⎞−⎜ ⎟⎝ ⎠

)

at x = a, Mx = Pab

L and at x = L, Mx = 0

(x) A Simply supported beam with two concentrated load ‘P’ from a distance ‘a’ both end.

The loading is shown below diagram


Chapter-4 Bending Moment and Shear Force Diagram S K Mondal’s Take a section at a distance x from the left support. This section is applicable for any value of x just to the

left of the applied force P. The shear, remains constant and is +P. The bending moment varies linearly from

the support, reaching a maximum of +Pa.

A section applicable anywhere between the two applied forces. Shear force is not necessary to maintain

equilibrium of a segment in this part of the beam. Only a constant bending moment of +Pa must be resisted

by the beam in this zone.

Such a state of bending or flexure is called pure bending.

Shear and bending-moment diagrams for this loading condition are shown below.

(xi) A Simply supported beam with a uniformly distributed load (UDL) through out its length

We will solve this problem by following two alternative ways.

(a) By Method of Section

Considering equilibrium we get RA = RB = wL2

Now Consider any cross-section XX which is at a distance x from left end A.


Chapter-4 Bending Moment and Shear Force Diagram S K Mondal’s Then the section view

Shear force: Vx = wL wx2

−

(i.e. S.F. variation is linear)

at x = 0, Vx = wL2

at x = L/2, Vx = 0

at x = L, Vx = -wL2

Bending moment: 2

.2 2x

wL wxM x= −

(i.e. B.M. variation is parabolic) at x = 0, Mx = 0

at x = L, Mx = 0

Now we have to determine maximum bending

moment and its position.

For maximum B.M: ( ) ( )

0 . . 0x xx x

d M d Mi e V V

dx dx⎡ ⎤

= = =⎢ ⎥⎣ ⎦∵

or 02 2

wL Lwx or x− = =

Therefore, maximum bending moment, =2

max 8wLM at x = L/2

(a) By Method of Integration

Shear force:

We know that, ( )xd V

wdx

= −

( )xor d V wdx= −

Integrating both side we get (at x =0, Vx =2

wL)



( )0

2

2

2

xV x

xwL

x

x

d V wdx

wLor V wx

wLor V wx

+

= −

− = −

= −

∫ ∫

Bending moment:

We know that, ( )x

x

d MV

dx=

( )2x x

wLor d M V dx wx dx⎛ ⎞= = −⎜ ⎟⎝ ⎠

Integrating both side we get (at x =0, Vx =0)

( )0

2

2

.2 2

xM x

xo

x

wLd M wx dx

wL wxor M x

⎛ ⎞= −⎜ ⎟⎝ ⎠

= −

∫ ∫

Let us take an example: A loaded beam as shown below. Draw its S.F and B.M diagram.

Considering equilibrium we get

( )A

B

M 0 gives

- 200 4 2 3000 4 R 8 0R 1700NBor

=

× × − × + × =

=

∑

A B

A

R R 200 4 3000R 2100N

Andor

+ = × +=

Now consider any cross-section which is at a distance 'x' from left end A andas shown in figure

XX



In the region 0 < x < 4m

Shear force (Vx) = RA – 200x = 2100 – 200 x

Bending moment (Mx) = RA .x – 200 x . x2

⎛ ⎞⎜ ⎟⎝ ⎠

= 2100 x -100 x2

at x = 0, Vx = 2100 N, Mx = 0

at x = 4m, Vx = 1300 N, Mx = 6800 N.m

In the region 4 m < x < 8 m

Shear force (Vx) = RA - 200 ×4 – 3000 = -1700

Bending moment (Mx) = RA. x - 200×4 (x-2) – 3000 (x- 4)

= 2100 x – 800 x + 1600 – 3000x +12000 = 13600 -1700 x

at x = 4 m, Vx = -1700 N, Mx = 6800 Nm

at x = 8 m, Vx = -1700 N, Mx = 0



(xii) A Simply supported beam with a gradually varying load (GVL) zero at one end and w/unit

length at other span.

Consider equilibrium of the beam =1 wL2

acting at a point C at a distance 2L/3 to the left end A.

B

A

A

BA

M 0 gives

wL LR .L - . 02 3wLor R6

wLSimilarly M 0 gives R3

=

=

=

= =

∑

∑

The free body diagram of section A - XX as shown below, Load at section XX, (wx) =w xL



The resulted of that part of the distributed load which acts on this free body is ( )21 w wxx . x

2 L 2L= = applied

at a point Z, distance x/3 from XX section.

Shear force (Vx) = 2 2

Awx wL wxR - - 2L 6 2L

=

Therefore the variation of shear force is parabolic

at x = 0, Vx = wL6

at x = L, Vx = -wL3

= − = −2 3wL wx x wL wxand .x . .x

6 2L 3 6 6LxBending Moment (M )

The variation of BM is cubic at x = 0, Mx = 0

at x = L, Mx = 0

For maximum BM; ( ) ( )x x

x x

d M d M0 i.e. V 0 V

dx dx⎡ ⎤

= = =⎢ ⎥⎣ ⎦∵

2

3 2

max

wL wx Lor - 0 or x6 2L 3

wL L w L wLand M6 6L3 3 9 3

= =

⎛ ⎞ ⎛ ⎞= × − × =⎜ ⎟ ⎜ ⎟⎝ ⎠ ⎝ ⎠

i.e. =2

maxwLM9 3

Lat x3

=



(xiii) A Simply supported beam with a gradually varying load (GVL) zero at each end and w/unit

length at mid span.

Consider equilibrium of the beam AB total load on the beam 1 L wL2 w2 2 2

⎛ ⎞= × × × =⎜ ⎟⎝ ⎠

A BwLTherefore R R4

= =

The free body diagram of section A –XX as shown below, load at section XX (wx) 2w .xL

=

The resultant of that part of the distributed load which acts on this free body is 21 2w wx.x. .x

2 L L= =

applied at a point, distance x/3 from section XX.

Shear force (Vx):

In the region 0 < x < L/2



( )2 2

x Awx wL wxV RL 4 L

= − = −

Therefore the variation of shear force is parabolic.

at x = 0, Vx = wL4

at x = L/4, Vx = 0

In the region of L/2 < x < L

The Diagram will be Mirror image of AC.

Bending moment (Mx):

In the region 0 < x < L/2

( )3

xwL 1 2wx wL wxM .x .x. . x / 3 -4 2 L 4 3L

⎛ ⎞= − =⎜ ⎟⎝ ⎠

The variation of BM is cubic

at x = 0, Mx = 0

at x = L/2, Mx =2wL

12


BM diagram will be mirror image of AC.

For maximum bending moment

( ) ( )x xx x

d M d M0 i.e. V 0 V

dx dx⎡ ⎤

= = =⎢ ⎥⎣ ⎦∵

2

2

max

wL wx Lor - 0 or x4 L 2

wLand M12

= =

=

i.e. =2

maxwLM12

Lat x2

=



(xiv) A Simply supported beam with a gradually varying load (GVL) zero at mid span and w/unit

length at each end.

We now superimpose two beams as

(1) Simply supported beam with a UDL through at its length

( )

( )

x 1

2

x 1

wLV wx2wL wxM .x2 2

= −

= −

And (2) a simply supported beam with a gradually varying load (GVL) zero at each end and w/unit length at

mind span.

In the range 0 < x < L/2

( )

( )

2

x 2

3

x 2

wL wxV4 LwL wxM .x4 3L

= −

= −

Now superimposing we get

Shear force (Vx):

In the region of 0< x < L/2



( ) ( )

( )

2

x x x1 2

2

wL wL wxV V V -wx -2 4 L

w x - L/2L

⎛ ⎞⎛ ⎞= − = − ⎜ ⎟⎜ ⎟⎝ ⎠ ⎝ ⎠

=

Therefore the variation of shear force is parabolic

at x = 0, Vx = +wL4

at x = L/2, Vx = 0

In the region L/2 < x < L The diagram will be mirror image of AC

Bending moment (Mx) = ( )x 1M - ( )x 2

M =

⎛ ⎞ ⎛ ⎞

= − − − = − +⎜ ⎟ ⎜ ⎟⎝ ⎠ ⎝ ⎠

2 3 3 2wL wx wL wx wx wx wL.x .x .x2 2 4 3L 3L 2 4

The variation of BM is cubic

x

2

x

at x 0, M 0

wxat x L / 2, M24

= =

= =

(xv) A simply supported beam with a gradually varying load (GVL) w1/unit length at one end and w2/unit length at other end.


Chapter-4 Bending Moment and Shear Force Diagram S K Mondal’s At first we will treat this problem by considering a UDL of identifying (w1)/unit length over the whole

length and a varying load of zero at one end to (w2- w1)/unit length at the other end. Then superimpose the

two loadings.

Consider a section XX at a distance x from left end A

(i) Simply supported beam with UDL (w1) over whole length

( )

( )

1x 11

21x 11

w LV w x2

w L 1M .x w x2 2

= −

= −

And (ii) simply supported beam with (GVL) zero at one end (w2- w1) at other end gives

( ) ( ) ( )

( ) ( ) ( )

22 1 2 1

2

32 1

2 12

6 2

. .6 6

x

x

w w w w xV

Lw w xLM w w x

L

− −= −

−= − −

Now superimposing we get

Shear force ( ) ( ) ( ) ( )= = − − −2

1 2x x 1 2 11 2

w L w L xV + V + w x w w3 6 2LxV

The SF variation is parabolic∴

( )

( )

1 2x 1 2

x 1 2

w L w L Lat x 0, V 2w w3 6 6Lat x L, V w 2w6

= = + = +

= = − +

Bending moment ( ) ( ) ( ) ⎛ ⎞= + = + − − ⎜ ⎟⎝ ⎠

2 31 1 2 1x x 11 2

w L w L w -w1M M .x .x w x .x3 6 2 6LxM

The BM variation is cubic.∴

x

x

at x 0, M 0at x L, M 0

= == =



(xvi) A Simply supported beam carrying a continuously distributed load. The intensity of the

load at any point is, π⎛ ⎞= ⎜ ⎟⎝ ⎠

sinxxw w

L. Where ‘x’ is the distance from each end of the beam.

We will use Integration method as it is easier in this case.

We know that ( ) ( )x x

x

d V d Mload and V

dx dx= =

( )

( )

π

π

⎛ ⎞= − ⎜ ⎟⎝ ⎠⎛ ⎞= − ⎜ ⎟⎝ ⎠

x

x

d VTherefore sin

dx L

d V sin dxL

xw

xw

( )

[ ]

ππ π

π π

⎛ ⎞⎜ ⎟⎛ ⎞ ⎛ ⎞⎝ ⎠= − = + + = + +⎜ ⎟ ⎜ ⎟

⎝ ⎠ ⎝ ⎠

=

∫ ∫x x

Integrating both side we getxw cos

x wL xLd V w sin dx or V A cosL L

Lwhere, constant of Integration

A

A



( ) ( ) ππ

πππ

π π

⎧ ⎫⎛ ⎞= = = +⎨ ⎬⎜ ⎟⎝ ⎠⎩ ⎭

⎛ ⎞⎜ ⎟ ⎛ ⎞⎝ ⎠= + = +⎜ ⎟

⎝ ⎠

xx x x

2

x 2

Again we know thatd M wL xV or d M V dx cos dx

dx LIntegrating both side we get

wL xsinwL xLM x + B sin x + B

LL

A

A A

[Where B = constant of Integration]

Now apply boundary conditions

At x = 0, Mx = 0 and at x = L, Mx = 0

This gives A = 0 and B = 0

( )x max

2

x 2

2

max 2

wL x wL Shear force V cos and V at x 0L

wL xAnd M sinL

wLM at x = L/2

ππ π

ππ

π

⎛ ⎞∴ = = =⎜ ⎟⎝ ⎠

⎛ ⎞= ⎜ ⎟⎝ ⎠

∴ =

(xvii) A Simply supported beam with a couple or moment at a distance ‘a’ from left end.

Considering equilibrium we get


Chapter-4 Bending Moment and Shear Force Diagram S K Mondal’s A

B B

B

A A

M 0 givesMR ×L+M 0 RL

and M 0 givesMR ×L+M 0 RL

or

or

=

= = −

=

− = =

∑

∑

Now consider any cross-section XX which is at a distance ‘x’ from left end A and another section YY at a

distance ‘x’ from left end A as shown in figure.

In the region 0 < x < a

Shear force (Vx) = RA = ML

Bending moment (Mx) = RA.x = ML

.x

In the region a< x < L

Shear force (Vx) = RA = ML

Bending moment (Mx) = RA.x – M = ML

.x - M



(xviii) A Simply supported beam with an eccentric load

When the beam is subjected to an eccentric load, the eccentric load is to be changed into a couple = Force×(distance travel by force) = P.a (in this case) and a force = P Therefore equivalent load diagram will be

Considering equilibrium

AM 0 gives=∑

-P.(L/2) + P.a + RB ×L = 0

or RB =P P.a2 L

− and RA + RB = P gives RA = P P.a2 L

+

Now consider any cross-section XX which is at a distance ‘x’ from left end A and another section YY at a distance ‘x’ from left end A as shown in figure.


Chapter-4 Bending Moment and Shear Force Diagram S K Mondal’s In the region 0 < x < L/2

Shear force (Vx) =P P.a2 L

+

Bending moment (Mx) = RA . x = P Pa2 L

⎛ ⎞+⎜ ⎟⎝ ⎠

. x


Shear force (Vx) =P Pa P PaP = -2 L 2 L

+ − +

Bending moment (Vx) = RA . x – P.( x - L/2 ) – M

= PL P Pa .x - Pa2 2 L

⎛ ⎞− −⎜ ⎟⎝ ⎠

4.6 Bending Moment diagram of Statically Indeterminate beam Beams for which reaction forces and internal forces cannot be found out from static equilibrium equations alone are called statically indeterminate beam. This type of beam requires deformation equation in addition to static equilibrium equations to solve for unknown forces.

Statically determinate - Equilibrium conditions sufficient to compute reactions.

Statically indeterminate - Deflections (Compatibility conditions) along with equilibrium equations

should be used to find out reactions.

Type of Loading & B.M Diagram Reaction Bending Moment



RA= RB = P2

MA = MB = PL-8

RA = RB =wL2

MA= MB =

2wL-12

2

A 3

2

3

R (3 )

(3 )B

Pb a bL

PaR b aL

= +

= +

MA = -2

2

PabL

−

MB = -2

2

Pa bL

−

RA= RB = 316wL

Rc = 5

8wL

R A RB

+--


Chapter-4 Bending Moment and Shear Force Diagram S K Mondal’s 4.7 Load and Bending Moment diagram from Shear Force diagram OR Load and Shear Force diagram from Bending Moment diagram

If S.F. Diagram for a beam is given, then

(i) If S.F. diagram consists of rectangle then the load will be point load

(ii) If S.F diagram consists of inclined line then the load will be UDL on that portion

(iii) If S.F diagram consists of parabolic curve then the load will be GVL

(iv) If S.F diagram consists of cubic curve then the load distribute is parabolic.

After finding load diagram we can draw B.M diagram easily.

If B.M Diagram for a beam is given, then

(i) If B.M diagram consists of inclined line then the load will be free point load

(ii) If B.M diagram consists of parabolic curve then the load will be U.D.L.

(iii) If B.M diagram consists of cubic curve then the load will be G.V.L.

(iv) If B.M diagram consists of fourth degree polynomial then the load distribution is parabolic.

Let us take an example: Following is the S.F diagram of a beam is given. Find its loading diagram.

Answer: From A-E inclined straight line so load will be UDL and in AB = 2 m length load = 6 kN if UDL is

w N/m then w.x = 6 or w×2 = 6 or w = 3 kN/m after that S.F is constant so no force is there. At last a 6 kN

for vertical force complete the diagram then the load diagram will be

As there is no support at left end it must be a cantilever beam.


Chapter-4 Bending Moment and Shear Force Diagram S K Mondal’s 4.8 Point of Contraflexure In a beam if the bending moment changes sign at a point, the point itself having zero bending moment, the

beam changes curvature at this point of zero bending moment and this point is called the point of contra

flexure.

Consider a loaded beam as shown below along with the B.M diagrams and deflection diagram.

In this diagram we noticed that for the beam loaded as in this case, the bending moment diagram is partly

positive and partly negative. In the deflected shape of the beam just below the bending moment diagram shows that left hand side of the beam is ‘sagging' while the right hand side of the beam is ‘hogging’.

The point C on the beam where the curvature changes from sagging to hogging is a point of contraflexure.

• There can be more than one point of contraflexure in a beam.

4.9 General expression

• EI4

2 ω= −d ydx

• 3

3 xd yEI Vdx

=

• 2

2 xd yEI Mdx

=

• dy = θ = slopedx

• y=δ = Deflection

• Flexural rigidity = EI





Shear Force (S.F.) and Bending Moment (B.M.) GATE-1. A concentrated force, F is applied

(perpendicular to the plane of the figure) on the tip of the bent bar shown in Figure. The equivalent load at a section close to the fixed end is:

(a) Force F (b) Force F and bending moment FL (c) Force F and twisting moment FL (d) Force F bending moment F L, and twisting

moment FL [GATE-1999]

GATE-2. The shear force in a beam subjected to pure positive bending is……

(positive/zero/negative) [GATE-1995] GATE-2(i) For the cantilever bracket, PQRS, loaded as shown in the adjoining figure(PQ = RL =

L, and QR = 2L), which of the following statements is FALSE? [CE: GATE-2011]

R S

P

Fixed

W

L

Q

2L

(a) The portion RS has a constant twisting moment with a value of 2WL (b) The portion QR has a varying twisting moment with a maximum value of WL. (c) The portiona PQ has a varying bending moment with a maximum value of WL (d) The portion PQ has no twisting moment

Cantilever GATE-3. Two identical cantilever beams are supported as shown, with their free ends in

contact through a rigid roller. After the load P is applied, the free ends will have [GATE-2005]

(a) Equal deflections but not equal slopes (b) Equal slopes but not equal deflections (c) Equal slopes as well as equal deflections (d) Neither equal slopes nor equal deflections


Chapter-4 Bending Moment and Shear Force Diagram S K Mondal’s GATE-4. A beam is made up of two

identical bars AB and BC, by hinging them together at B. The end A is built-in (cantilevered) and the end C is simply-supported. With the load P acting as shown, the bending moment at A is:

[GATE-2005]

(a) Zero (b) PL2

(c) 3PL

2 (d) Indeterminate

Cantilever with Uniformly Distributed Load GATE-5. The shapes of the bending moment diagram for a uniform cantilever beam carrying a

uniformly distributed load over its length is: [GATE-2001] (a) A straight line (b) A hyperbola (c) An ellipse (d) A parabola

Cantilever Carrying load Whose Intensity varies GATE-6. A cantilever beam carries the anti-

symmetric load shown, where ωo is the peak intensity of the distributed load. Qualitatively, the correct bending moment diagram for this beam is:

[GATE-2005]

Simply Supported Beam Carrying Concentrated Load GATE-7. A concentrated load of P acts on a simply supported beam of span L at a distance

3L

from the left support. The bending moment at the point of application of the load is given by [GATE-2003]

2 2( ) ( ) ( ) ( )

3 3 9 9PL PL PL PLa b c d


Chapter-4 Bending Moment and Shear Force Diagram S K Mondal’s GATE-8. A simply supported beam carries a load 'P'

through a bracket, as shown in Figure. The maximum bending moment in the beam is

(a) PI/2 (b) PI/2 + aP/2 (c) PI/2 + aP (d) PI/2 – aP

[GATE-2000]

Simply Supported Beam Carrying a Uniformly Distributed Load Statement for Linked Answer and Questions Q9-Q10: A mass less beam has a loading pattern as shown in the figure. The beam is of rectangular cross-section with a width of 30 mm and height of 100 mm. [GATE-2010]

GATE-9. The maximum bending moment occurs at (a) Location B (b) 2675 mm to the right of A (c) 2500 mm to the right of A (d) 3225 mm to the right of A GATE-10. The maximum magnitude of bending stress (in MPa) is given by (a) 60.0 (b) 67.5 (c) 200.0 (d) 225.0 Data for Q11-Q12 are given below. Solve the problems and choose correct answers A steel beam of breadth 120 mm and height 750 mm is loaded as shown in the figure. Assume Esteel= 200 GPa.

[GATE-2004]

GATE-11. The beam is subjected to a maximum bending moment of (a) 3375 kNm (b) 4750 kNm (c) 6750 kNm (d) 8750 kNm GATE-12. The value of maximum deflection of the beam is: (a) 93.75 mm (b) 83.75 mm (c) 73.75 mm (d) 63.75 mm Statement for Linked Answer and Questions Q13-Q14: A simply supported beam of span length 6m and 75mm diameter carries a uniformly distributed load of 1.5 kN/m [GATE-2006] GATE-13. What is the maximum value of bending moment? (a) 9 kNm (b) 13.5 kNm (c) 81 kNm (d) 125 kNm GATE-14. What is the maximum value of bending stress? (a) 162.98 MPa (b) 325.95 MPa (c) 625.95 MPa (d) 651.90 MPa Common Data for Question 14(i) and 14(ii): A three-span continuous beam has an internal hinge at B. Section B is at the mid-span of AC, Section E is at the mid-span of CG. The 20 kN load is applied at section B whereas 10 kN loads are applied at sections D and F as shown in the figure. Span GH is subjected to uniformly


Chapter-4 Bending Moment and Shear Force Diagram S K Mondal’s distributed load of magnitude 5 kN/m. For the loading shown, shear force immediate to the right of section E is 9.84 kN upwards and the hogging moment at section E is 10.31 kN-m

[CE: GATE-2004]

4 m4 m4 m

A B

C

D

E

F

G

20 kN 10 kN 10 kN 5 kN /m

H

GATE-14(i)The magnitude of the shear force immediate to the left and immediate to the right of

section B are, respectively [CE: GATE-2004] (a) 0 and 20 kN (b) 10 kN and 10 kN (c) 20 kN and 0 (d) 9.84 kN and 10.16 kN GATE-14(ii)The vertical reaction at support H is [CE: GATE-2004] (a) 15 kN upward (b) 9.84 kN upward (c) 15 kN downward (d) 9.84 downward

Simply Supported Beam Carrying a Load whose Intensity varies Uniformly from Zero at each End to w per Unit Run at the MiD Span GATE-16. A simply supported beam of length 'l' is subjected to a symmetrical uniformly varying

load with zero intensity at the ends and intensity w (load per unit length) at the mid span. What is the maximum bending moment? [IAS-2004]

(a) 23

8wl

(b)2

12wl

(c) 2

24wl

(d) 25

12wl

GATE-16(i)For the simply supported beam of length L, subjected toa uniformly distributed

moment M kN-m per unit length as shown in the figure, the bending moment (in kN-m) at the mid-span of the beam is [CE: GATE-2010]

L

M kN-m per unit length

(a) zero (b) M (c) ML (d) ML

GATE-16(ii) A simply supported beam of length L is subjected to a varying distributed load ( / ) Nm-1, where the distance x is measured from the left support. The

magnitude of the vertical reaction force in N at the left support is [GATE-2013] (a) zero (b) L/3π (c) L/π (d) 2L/π

GATE-17. List-I shows different loads acting on a beam and List-II shows different bending

moment distributions. Match the load with the corresponding bending moment diagram.

List-I List-II [CE: GATE-2003] A. 1.



B. 2.

C. 3.

D. 4.

5.

Codes A B C D A B C D (a) 4 2 1 3 (b) 5 4 1 3 (c) 2 5 3 1 (d) 2 4 1 3 GATE-18. The bending moment diagram for a beam is given below: [CE: GATE-2005]

100 kN-m

200 kN-ma

b

b′a′

0.5m0.5m 1m 1m The shear force at sections andaa bb′ ′ respectively are of the magnitude. (a) 100 kN, 150 kN (b) zero, 100 kN (c) zero, 50 kN (d) 100 kN, 100 kN GATE-19. A simply supported beam AB has the bending moment diagram as shown in the

following figure: [CE: GATE-2006]

L L L

A B

M

M

M

D

The beam is possibly under the action of following loads (a) Couples of M at C and 2M at D (b) Couples of 2M at C and M at D



(c) Concentrated loads of ML

at C and 2ML

at D

(d) Concentrated loads of ML

at C and couple of 2M at D

GATE-20. Match List-I (Shear Force Diagrams) beams with List-II (Diagrams of beams with

supports and loading) and select the correct answer by using the codes given below the lists: [CE: GATE-2009]

List-I List-II A.

qL4

qL4 +

–

+

– qL2

qL2

B.

qL4

qL4 +

–

C.

q2

q2

q2

q2

q2 +

–+

–

q2q2

q2q2

q2q2

D.

q2

q2q2

+–

1

L4

L4L

q/unit length q/unit length

2.

L4

q2

L4L

q2

q2q2 q

3.

L4

L4L

q/unit length

4.

L4

q2

L4L

q2

q2q2

Codes: A B C D A B C D (a) 3 1 2 4 (b) 3 4 2 1 (c) 2 1 4 3 (d) 2 4 3 1


Shear Force (S.F.) and Bending Moment (B.M.) IES-1. A lever is supported on two

hinges at A and C. It carries a force of 3 kN as shown in the above figure. The bending moment at B will be

(a) 3 kN-m (b) 2 kN-m (c) 1 kN-m (d) Zero


Chapter-4 Bending Moment and Shear Force Diagram S K Mondal’s [IES-1998]

IES-2. A beam subjected to a load P is shown in the given figure. The bending moment at the support AA of the beam will be

(a) PL (b) PL/2 (c) 2PL (d) zero

[IES-1997]

IES-3. The bending moment (M) is constant over a length segment (I) of a beam. The shearing force will also be constant over this length and is given by [IES-1996]

(a) M/l (b) M/2l (c) M/4l (d) None of the above IES-4. A rectangular section beam subjected to a bending moment M varying along its

length is required to develop same maximum bending stress at any cross-section. If the depth of the section is constant, then its width will vary as [IES-1995]

(a) M (b) M (c) M2 (d) 1/M IES-5. Consider the following statements: [IES-1995] If at a section distant from one of the ends of the beam, M represents the bending

moment. V the shear force and w the intensity of loading, then 1. dM/dx = V 2. dV/dx = w 3. dw/dx = y (the deflection of the beam at the section) Select the correct answer using the codes given below: (a) 1 and 3 (b) 1 and 2 (c) 2 and 3 (d) 1, 2 and 3 IES-5a Shear force and

bending moment diagrams for a beam ABCD are shown in figure. It can be concluded that

(a) The beam has three supports

(b) End A is fixed (c) A couple of 2000

Nm acts at C (d) A uniformly

distributed load is confined to portion BC only

300 N

200 N

10 m 25 m

A DB C

3000 Nm

10 m 10 m 15 m

1000 Nm

3000 Nm

A B C D

[IES-2010]

Cantilever IES-6. The given figure shows a beam BC simply supported at C and hinged at B (free end)

of a cantilever AB. The beam and the cantilever carry forces of

100 kg and 200 kg respectively. The bending moment at B is: [IES-1995] (a) Zero (b) 100 kg-m (c) 150 kg-m (d) 200 kg-m IES-7. Match List-I with List-II and select the correct answer using the codes given below

the lists: [IES-1993, 2011] List-I List-II (Condition of beam) (Bending moment diagram)


Chapter-4 Bending Moment and Shear Force Diagram S K Mondal’s A. Subjected to bending moment at the 1. Triangle end of a cantilever B. Cantilever carrying uniformly distributed 2. Cubic parabola load over the whole length C. Cantilever carrying linearly varying load 3. Parabola from zero at the fixed end to maximum at the support D. A beam having load at the centre and 4. Rectangle supported at the ends Codes: A B C D A B C D (a) 4 1 2 3 (b) 4 3 2 1 (c) 3 4 2 1 (d) 3 4 1 2 IES-8. If the shear force acting at every section of a beam is of the same magnitude and of

the same direction then it represents a [IES-1996] (a) Simply supported beam with a concentrated load at the centre. (b) Overhung beam having equal overhang at both supports and carrying equal concentrated

loads acting in the same direction at the free ends. (c) Cantilever subjected to concentrated load at the free end. (d) Simply supported beam having concentrated loads of equal magnitude and in the same

direction acting at equal distances from the supports.

Cantilever with Uniformly Distributed Load IES-9. A uniformly distributed load ω (in kN/m) is acting over the entire length of a 3 m long

cantilever beam. If the shear force at the midpoint of cantilever is 6 kN, what is the value of ω ? [IES-2009]

(a) 2 (b) 3 (c) 4 (d) 5 IES-10. Match List-I with List-II and select the correct answer using the code given below the

Lists: [IES-2009]

Code: A B C D A B C D (a) 1 5 2 4 (b) 4 5 2 3 (c) 1 3 4 5 (d) 4 2 5 3


Chapter-4 Bending Moment and Shear Force Diagram S K Mondal’s IES-11. The shearing force diagram for a

beam is shown in the above figure. The bending moment diagram is represented by which one of the following?

[IES-2008]

IES-12. A cantilever beam having 5 m length is so loaded that it develops a shearing force of

20T and a bending moment of 20 T-m at a section 2m from the free end. Maximum shearing force and maximum bending moment developed in the beam under this load are respectively 50 T and 125 T-m. The load on the beam is: [IES-1995]

(a) 25 T concentrated load at free end (b) 20T concentrated load at free end (c) 5T concentrated load at free end and 2 T/m load over entire length (d) 10 T/m udl over entire length

Cantilever Carrying Uniformly Distributed Load for a Part of its Length IES-13. A vertical hanging bar of length L and weighing w N/ unit length carries a load W at

the bottom. The tensile force in the bar at a distance Y from the support will be given by [IES-1992]

( ) ( ) ( )( ) ( )a b ( ) c / d ( ) WW wL W w L y W w y L W L yw

+ + − + + −

Cantilever Carrying load Whose Intensity varies IES-14. A cantilever beam of 2m length supports a triangularly distributed load over its

entire length, the maximum of which is at the free end. The total load is 37.5 kN.What is the bending moment at the fixed end? [IES 2007]

(a) 50×106 N mm (b) 12.5× 106 N mm (c) 100 ×106 N mm (d) 25×106 N mm

Simply Supported Beam Carrying Concentrated Load IES-15. Assertion (A): If the bending moment along the length of a beam is constant, then the

beam cross section will not experience any shear stress. [IES-1998] Reason (R): The shear force acting on the beam will be zero everywhere along the

length. (a) Both A and R are individually true and R is the correct explanation of A (b) Both A and R are individually true but R is NOT the correct explanation of A


Chapter-4 Bending Moment and Shear Force Diagram S K Mondal’s (c) A is true but R is false (d) A is false but R is true IES-16. Assertion (A): If the bending moment diagram is a rectangle, it indicates that the

beam is loaded by a uniformly distributed moment all along the length. Reason (R): The BMD is a representation of internal forces in the beam and not the

moment applied on the beam. [IES-2002] (a) Both A and R are individually true and R is the correct explanation of A (b) Both A and R are individually true but R is NOT the correct explanation of A (c) A is true but R is false (d) A is false but R is true IES-17. The maximum bending moment in a simply supported beam of length L loaded by a

concentrated load W at the midpoint is given by [IES-1996]

(a) WL (b) 2

WL (c)

4WL

(d) 8

WL

IES-18. A simply supported beam is

loaded as shown in the above figure. The maximum shear force in the beam will be

(a) Zero (b) W (c) 2W (d) 4W

[IES-1998] IES-19. If a beam is subjected to a constant bending moment along its length, then the shear

force will [IES-1997] (a) Also have a constant value everywhere along its length (b) Be zero at all sections along the beam (c) Be maximum at the centre and zero at the ends (d) zero at the centre and maximum at

the ends IES-20. A loaded beam is shown in

the figure. The bending moment diagram of the beam is best represented as:

[IES-2000]

IES-21. A simply supported beam has equal over-hanging lengths and carries equal

concentrated loads P at ends. Bending moment over the length between the supports [IES-2003]

(a) Is zero (b) Is a non-zero constant (c) Varies uniformly from one support to the other (d) Is maximum at mid-span IES-21(i). A beam simply supported at equal distance from the ends carries equal loads at each

end. Which of the following statements is true? [IES-2013] (a) The bending moment is minimum at the mid-span


Chapter-4 Bending Moment and Shear Force Diagram S K Mondal’s (b) The bending moment is minimum at the support (c) The bending moment varies gradually between the supports (d) The bending moment is uniform between the supports IES-22. The bending moment diagram for the case shown below will be q as shown in

(a)

(b)

(c)

(d)

[IES-1992]

IES-23. Which one of the following portions of the loaded beam shown in the given figure is subjected to pure bending?

(a) AB (b)DE (c) AE (d) BD

[IES-1999] IES-24. Constant bending moment over span "l" will occur in [IES-1995]

IES-25. For the beam shown in the above

figure, the elastic curve between the supports B and C will be:

(a) Circular (b) Parabolic (c) Elliptic (d) A straight line

[IES-1998] IES-26. A beam is simply supported at its ends and is loaded by a couple at its mid-span as

shown in figure A. Shear force diagram for the beam is given by the figure. [IES-1994]

(a) B (b) C (c) D (d) E


Chapter-4 Bending Moment and Shear Force Diagram S K Mondal’s IES-27. A beam AB is hinged-supported at its ends and is loaded by couple P.c. as shown in

the given figure. The magnitude or shearing force at a section x of the beam is: [IES-1993]

(a) 0 (b) P (c) P/2L (d) P.c./2L

Simply Supported Beam Carrying a Uniformly Distributed Load IES-28. A freely supported beam at its ends carries a central concentrated load, and maximum bending

moment is M. If the same load be uniformly distributed over the beam length, then what is the maximum bending moment? [IES-2009]

(a) M (b) 2M

(c) 3M

(d) 2M

Simply Supported Beam Carrying a Load who’s Intensity varies uniformly from Zero at each End to w per Unit Run at the MiD Span

IES-29. A simply supported beam is subjected to a distributed loading as shown in the diagram given below:

What is the maximum shear force in the beam?

(a) WL/3 (b) WL/2 (c) 2WL/3 (d) WL/4

[IES-2004]

Simply Supported Beam carrying a Load who’s Intensity varies IES-30. A beam having uniform cross-section carries a uniformly distributed load of intensity

q per unit length over its entire span, and its mid-span deflection is δ.

The value of mid-span deflection of the same beam when the same load is distributed with intensity varying from 2q unit length at one end to zero at the other end is: [IES-1995]

(a) 1/3 δ (b) 1/2 δ (c) 2/3 δ (d) δ

Simply Supported Beam with Equal Overhangs and carrying a Uniformly Distributed Load IES-31. A beam, built-in at both ends, carries a uniformly distributed load over its entire

span as shown in figure-I. Which one of the diagrams given below, represents bending moment distribution along the length of the beam?

[IES-1996]



The Points of Contraflexure IES-32. The point· of contraflexure is a point where: [IES-2005] (a) Shear force changes sign (b) Bending moment changes sign (c) Shear force is maximum (d) Bending moment is maximum IES-33. Match List I with List II and select the correct answer using the codes given below

the Lists: [IES-2000] List-I List-II A. Bending moment is constant 1. Point of contraflexure B. Bending moment is maximum or minimum 2. Shear force changes sign C. Bending moment is zero 3. Slope of shear force diagram is zero over the portion of the beam D. Loading is constant 4. Shear force is zero over the portion of the beam Code: A B C D A B C D (a) 4 1 2 3 (b) 3 2 1 4 (c) 4 2 1 3 (d) 3 1 2 4

Loading and B.M. diagram from S.F. Diagram IES-34. The bending moment diagram shown in Fig. I correspond to the shear force diagram

in [IES-1999]

IES-35. Bending moment distribution in a built beam is shown in the given

The shear force distribution in the beam is represented by [IES-2001]



IES-36. The given figure shows the

shear force diagram for the beam ABCD.

Bending moment in the portion BC of the beam

[IES-1996] (a) Is a non-zero constant (b) Is zero (c) Varies linearly from B to C (d) Varies parabolically from B to C IES-37. Figure shown above represents the

BM diagram for a simply supported beam. The beam is subjected to which one of the following?

(a) A concentrated load at its mid-length

(b) A uniformly distributed load over its length

(c) A couple at its mid-length (d) Couple at 1/4 of the span from each

end

[IES-2006] IES-38. If the bending moment diagram for

a simply supported beam is of the form given below.

Then the load acting on the beam is:

(a) A concentrated force at C (b) A uniformly distributed load over

the whole length of the beam (c) Equal and opposite moments

applied at A and B (d) A moment applied at C

[IES-1994] IES-39. The figure given below shows a bending moment diagram for the beam CABD:

Load diagram for the above beam will be: [IES-1993]



IES-40. The shear force diagram shown in the following figure is that of a [IES-1994] (a) Freely supported beam with symmetrical point load about mid-span. (b) Freely supported beam with symmetrical uniformly distributed load about mid-span (c) Simply supported beam with positive and negative point loads symmetrical about the mid-

span (d) Simply supported beam with symmetrical varying load about mid-span

Statically Indeterminate beam IES-41 Which one of the following is NOT a statically indeterminate structure?

AC B

T

(a)

P

BAC

(b)

TX

Y

Z

O

(c) Steel

AliminiumF(d)

[IES-2010]


Shear Force (S.F.) and Bending Moment (B.M.) IAS-1. Assertion (A): A beam subjected only to end moments will be free from shearing force.

[IAS-2004] Reason (R): The bending moment variation along the beam length is zero.


Chapter-4 Bending Moment and Shear Force Diagram S K Mondal’s (a) Both A and R are individually true and R is the correct explanation of A (b) Both A and R are individually true but R is NOT the correct explanation of A (c) A is true but R is false (d) A is false but R is true IAS-2. Assertion (A): The change in bending moment between two cross-sections of a beam is

equal to the area of the shearing force diagram between the two sections.[IAS-1998] Reason (R): The change in the shearing force between two cross-sections of beam due

to distributed loading is equal to the area of the load intensity diagram between the two sections.

(a) Both A and R are individually true and R is the correct explanation of A (b) Both A and R are individually true but R is NOT the correct explanation of A (c) A is true but R is false (d) A is false but R is true IAS-3. The ratio of the area under the bending moment diagram to the flexural rigidity

between any two points along a beam gives the change in [IAS-1998] (a) Deflection (b) Slope (c) Shear force (d) Bending moment

Cantilever IAS-4. A beam AB of length 2 L having a

concentrated load P at its mid-span is hinge supported at its two ends A and B on two identical cantilevers as shown in the given figure. The correct value of bending moment at A is

(a) Zero (b) PLl2 (c) PL (d) 2 PL

[IAS-1995]

IAS-5. A load perpendicular to the plane of the handle is applied at the free end as shown in

the given figure. The values of Shear Forces (S.F.), Bending Moment (B.M.) and torque at the fixed end of the handle have been determined respectively as 400 N, 340 Nm and 100 by a student. Among these values, those of [IAS-1999]

(a) S.F., B.M. and torque are correct (b) S.F. and B.M. are correct (c) B.M. and torque are correct (d) S.F. and torque are correct

Cantilever with Uniformly Distributed Load IAS-6. If the SF diagram for a beam is a triangle with length of the beam as its base, the

beam is: [IAS-2007] (a) A cantilever with a concentrated load at its free end (b) A cantilever with udl over its whole span (c) Simply supported with a concentrated load at its mid-point (d) Simply supported with a udl over its whole span IAS-7. A cantilever carrying a uniformly distributed load is shown in Fig. I. Select the correct R.M. diagram of the cantilever. [IAS-1999]



IAS-8. A structural member ABCD is loaded

as shown in the given figure. The shearing force at any section on the length BC of the member is:

(a) Zero (b) P (c) Pa/k (d) Pk/a

[IAS-1996]

Cantilever Carrying load Whose Intensity varies IAS-9. The beam is loaded as shown in Fig. I. Select the correct B.M. diagram

[IAS-1999]

Simply Supported Beam Carrying Concentrated Load IAS-10. Assertion (A): In a simply supported beam carrying a concentrated load at mid-span,

both the shear force and bending moment diagrams are triangular in nature without any change in sign. [IAS-1999]

Reason (R): When the shear force at any section of a beam is either zero or changes sign, the bending moment at that section is maximum.

(a) Both A and R are individually true and R is the correct explanation of A (b) Both A and R are individually true but R is NOT the correct explanation of A (c) A is true but R is false (d) A is false but R is true IAS-11. For the shear force to be uniform throughout the span of a simply supported beam, it

should carry which one of the following loadings? [IAS-2007] (a) A concentrated load at mid-span (b) Udl over the entire span (c) A couple anywhere within its span (d) Two concentrated loads equal in magnitude and placed at equal distance from each

support IAS-12. Which one of the following figures represents the correct shear force diagram for the

loaded beam shown in the given figure I? [IAS-1998; IAS-1995]



Simply Supported Beam Carrying a Uniformly Distributed Load IAS-13. For a simply supported beam of length fl' subjected to downward load of uniform

intensity w, match List-I with List-II and select the correct answer using the codes given below the Lists: [IAS-1997]

List-I List-II

A. Slope of shear force diagram 1. 45

384wE Iι

B. Maximum shear force 2. w

C. Maximum deflection 3. 4

8wι

D. Magnitude of maximum bending moment 4. 2wι


Simply Supported Beam Carrying a Load whose Intensity varies Uniformly from Zero at each End to w per Unit Run at the MiD Span IAS-14. A simply supported beam of length 'l' is subjected to a symmetrical uniformly varying

load with zero intensity at the ends and intensity w (load per unit length) at the mid span. What is the maximum bending moment? [IAS-2004]

(a) 23

8wl

(b)2

12wl

(c) 2

24wl

(d) 25

12wl



Simply Supported Beam carrying a Load whose Intensity varies IAS-15. A simply supported beam of span l is subjected to a uniformly varying load having

zero intensity at the left support and w N/m at the right support. The reaction at the right support is: [IAS-2003]

(a)2wl

(b) 5wl

(c) 4wl

(d) 3wl

Simply Supported Beam with Equal Overhangs and carrying a Uniformly Distributed Load IAS-16. Consider the following statements for a simply supported beam subjected to a couple

at its mid-span: [IAS-2004] 1. Bending moment is zero at the ends and maximum at the centre 2. Bending moment is constant over the entire length of the beam 3. Shear force is constant over the entire length of the beam 4. Shear force is zero over the entire length of the beam

Which of the statements given above are correct? (a) 1, 3 and 4 (b) 2, 3 and 4 (c) 1 and 3 (d) 2 and 4 IAS-17. Match List-I (Beams) with List-II (Shear force diagrams) and select the correct

answer using the codes given below the Lists: [IAS-2001]


The Points of Contraflexure IAS-18. A point, along the length of a beam subjected to loads, where bending moment

changes its sign, is known as the point of [IAS-1996] (a) Inflexion (b) Maximum stress (c) Zero shear force (d) Contra flexure IAS-19. Assertion (A): In a loaded beam, if the shear force diagram is a straight line parallel

to the beam axis, then the bending moment is a straight line inclined to the beam axis. [IAS 1994]

Reason (R): When shear force at any section of a beam is zero or changes sign, the bending moment at that section is maximum.

(a) Both A and R are individually true and R is the correct explanation of A


Chapter-4 Bending Moment and Shear Force Diagram S K Mondal’s (b) Both A and R are individually true but R is NOT the correct explanation of A (c) A is true but R is false (d) A is false but R is true

Loading and B.M. diagram from S.F. Diagram IAS-20. The shear force diagram of a

loaded beam is shown in the following figure:

The maximum Bending Moment of the beam is:

(a) 16 kN-m (b) 11 kN-m

(c) 28 kN-m (d) 8 kN-m

[IAS-1997]

IAS-21. The bending moment for a loaded beam is shown below: [IAS-2003]

The loading on the beam is represented by which one of the followings diagrams?

(a)

(b)

(c)

(d)

IAS-22. Which one of the given bending moment diagrams correctly represents that of the

loaded beam shown in figure? [IAS-1997]


Chapter-4 Bending Moment and Shear Force Diagram S K Mondal’s IAS-23.

The shear force diagram is shown

above for a loaded beam. The

corresponding bending moment diagram is represented by

[IAS-2003]

IAS-24. The bending moment diagram for a simply supported beam is a rectangle over a

larger portion of the span except near the supports. What type of load does the beam carry? [IAS-2007]

(a) A uniformly distributed symmetrical load over a larger portion of the span except near the supports

(b) A concentrated load at mid-span (c) Two identical concentrated loads equidistant from the supports and close to mid-point of

the beam (d) Two identical concentrated loads equidistant from the mid-span and close to supports


Chapter-

GATE-1. GATE-2. GATE-2(GATE-3.

GATE-4. GATE-5.

GATE-6.

=2

xwxM

2 GATE-7.

GATE-8. GATE-9.

-4

Ans. (c) Ans. Zero i). AnsAns. (a) As

coAns. (b) Ans. (d)

Ans. (d)

−2 3wx

6L

Ans. (d)

cPabM

l=

Ans. (b) Ans. (c)

Bendi

O

s. (b) s it is rigid rontact. But s

LP3

L

⎛ ⎞ ⎛× ×⎜ ⎟ ⎜⎝ ⎠ ⎝=

ng Momen

BJEC

roller, deflecslope unequa

2L2PL3

9

⎛ ⎞⎟

⎝ ⎠ =

nt and Shea

CTIVE

ction must bal.

ar Force Di

ANSW

be same, bec

iagram

WERS

cause after d

S K

deflection th

Mondal’s

hey also will be in



R1 R2

3000 N/m

( ) {

+ = × =× − × × ==

− × − = >

=

1 2

1

1n

1

R R 3000 2 6000NR 4 3000 2 1 0R 1500,

S.F. eq . at any section x from end A.R 3000 x 2 0 for x 2m}x 2.5 m.

GATE-10. Ans. (b) Binding stress will be maximum at the outer surface So taking 9 = 50 mm

3

3

23

x

62500

6

3

50and &12

12

m 1.5 10 [2000 ]2

3.375 10

3.375 10 50 12 67.530 100

σ

σ

×= =

= × + −

∴ = × −

× × ×∴ = =×

ld mIdl

xx

m N mm

MPa

GATE-11. Ans. (a) 2 2

maxwl 120 15M kNm 3375kNm8 8

×= = =

GATE-12. Ans. (a) Moment of inertia (I) = ( )333 40.12 0.75bh 4.22 10 m

12 12−×

= = ×

4 3 4

max 9 3

5 wl 5 120 10 15 m 93.75mm384 EI 384 200 10 4.22 10

δ −

× ×= = × =× × ×

GATE-13. Ans. (a) 2 2

maxwl 1.5 6M 6.75kNm8 8

×= = = But not in choice. Nearest choice (a)

GATE-14. Ans. (a) ( )

3

3 2

32M 32 6.75 10 Pa 162.98MPad 0.075

σπ π

× ×= = =×

GATE-14(i) Ans. (a) The moment about B from left = 0 If × =AR 2 0 ⇒ =AR 0 ∴ Shear force immediate to the left of = =AB R 0 Shear force immediate to the right of = ↓B 20kN( ) GATE-14(ii) Ans.(b)



4 m1 m

E

F

G R G RH

10 kN 5 kN /m

10.31kN -m

9.84kN

H 1m

Taking moments about G × − × × + − × + × =HR 4 5 4 2 10.31 9.84 2 10 1 0

⇒ = =H39.37R 9.84 kN

4

GATE-16. Ans. (b) GATE-16(i). Ans. (a) Let the reaction at the right hand support be RV upwards. Taking moments about left hand

support, we get × − =RV L ML 0 ⇒ =RV M Thus, the reaction at the left hand support LV will be M downwards. ∴ Moment at the mid-span

= − × + × =L LM M 02 2

Infact the bending moment through out the beam is zero. GATE-16(ii) Ans. (b) GATE-17. Ans. (d)

GATE-18. Ans. (c) The bending moment to the left as well as right of section ′aa is constant which means shear

force is zero at ′.aa

Shear force at −′ = =200 100 50kN2

bb

GATE-19. Ans. (a) The shear force diagram is

R A R B

2M M

Loading diagram

A B C D

ML

ML

SFD

–

= = =A B3M MR R3L L

GATE-20. Ans. (a)



IES IES-1. Ans. (a)

IES-2. Ans. (b) Load P at end produces moment 2

PL in

anticlockwise direction. Load P at end produces moment of PL in clockwise direction. Net moment at AA is PL/2.

IES-3. Ans. (d) Dimensional analysis gives choice (d)

IES-4. Ans. (a) = =3M bhconst. and I

I 12

IES-5. Ans. (b) IES-5a Ans. (c) A vertical increase in BM diagram entails there is a point moment similarly a vertical increase in SF diagram entails there is a point shear force. IES-6. Ans. (a) IES-7. Ans. (b) IES-8. Ans. (c) IES-9. Ans. (c)

Shear force at mid point of cantilever

62

3 62

6 2 4 kN / m3

ω= =

ω×⇒ =

×⇒ ω = =

l

IES-10. Ans. (b) IES-11. Ans. (b) Uniformly distributed load on cantilever beam.

IES-12. Ans. (d) IES-13. Ans. (b) IES-14. Ans. (a)



M = 37.5×34

KNm = 50×106 Nmm

IES-15. Ans. (a) IES-16. Ans. (d) IES-17. Ans. (c) IES-18. Ans. (c) IES-19. Ans. (b) IES-20. Ans. (a) IES-21. Ans. (b)

IES-21(i). Ans. (d) IES-22. Ans. (a) IES-23. Ans. (d) Pure bending takes place in the section between two weights W IES-24. Ans. (d) IES-25. Ans. (b) IES-26. Ans. (d) IES-27. Ans. (d) If F be the shearing force at section x (at point A), then taking moments about B, F x 2L =

Pc

Thus shearing force in zone x2 2Pc Pcor FL L

= =

IES-28. Ans. (b)



MaxWLB.M M4

= =

Where the Load is U.D.L. Maximum Bending Moment

2W LL 8

WL 1 WL M8 2 4 2

⎛ ⎞⎛ ⎞= ⎜ ⎟⎜ ⎟⎝ ⎠ ⎝ ⎠

⎛ ⎞= = =⎜ ⎟⎝ ⎠

IES-29. Ans. (d)

2

x

max at x 0

1 WLTotal load L W2 2

WL 1 W WL WxS x. XL4 2 4 L2

WLS4=

= × × =

⎛ ⎞⎜ ⎟

= − × = −⎜ ⎟⎜ ⎟⎜ ⎟⎝ ⎠

=

IES-30. Ans. (d) IES-31. Ans. (d) IES-32. Ans. (b) IES-33. Ans. (b) IES-34. Ans. (b) If shear force is zero, B.M. will also be zero. If shear force varies linearly with length, B.M.

diagram will be curved line. IES-35. Ans. (a) IES-36. Ans. (a) IES-37. Ans. (c) IES-38. Ans. (d) A vertical line in centre of B.M. diagram is possible when a moment is applied there. IES-39. Ans. (a) Load diagram at (a) is correct because B.M. diagram between A and B is parabola which is

possible with uniformly distributed load in this region. IES-40. Ans. (b) The shear force diagram is possible on simply supported beam with symmetrical varying

load about mid span. IES-41 Ans. (c)



IAS IAS-1. Ans. (a) IAS-2. Ans. (b) IAS-3. Ans. (b) IAS-4. Ans. (a) Because of hinge support between beam AB and cantilevers, the bending moment can't be

transmitted to cantilever. Thus bending moment at points A and B is zero. IAS-5. Ans. (d)

( )S.F 400N and BM 400 0.4 0.2 240NmTorque 400 0.25 100Nm

= = × + =

= × =

IAS-6. Ans. (b)

IAS-7. Ans. (c)

2

xx wxM wx2 2

= − × = −

IAS-8. Ans. (a) IAS-9. Ans. (d) IAS-10. Ans. (d) A is false.

IAS-11. Ans. (c) IAS-12. Ans. (a) IAS-13. Ans. (d)



IAS-14. Ans. (b) IAS-15. Ans. (d) IAS-16. Ans. (c)

IAS-17. Ans. (d) IAS-18. Ans. (d) IAS-19. Ans. (b) IAS-20. Ans. (a)

IAS-21. Ans. (d) IAS-22. Ans. (c) Bending moment does not depends on moment of inertia. IAS-23. Ans. (a) IAS-24. Ans. (d)




Conventional Question IES-2005 Question: A simply supported beam of length 10 m carries a uniformly varying load whose

intensity varies from a maximum value of 5 kN/m at both ends to zero at the centre of the beam. It is desired to replace the beam with another simply supported beam which will be subjected to the same maximum 'bending moment’ and ‘shear force' as in the case of the previous one. Determine the length and rate of loading for the second beam if it is subjected to a uniformly distributed load over its whole length. Draw the variation of 'SF' and 'BM' in both the cases.

Answer:

10mR A R B

5KN/m 5KN/mX

X

B

10Total load on beam =5× 252

25 12.52

a section X-X from B at a distance x.For 0 x 5 we get rate of loading

[ lineary varying]at x=0, =5 /

at x = 5, 0These two bounday con

A B

kN

R R kN

Takem

a bx askN m

and

ωω

ω

=

∴ = = =

≤ ≤= +

=dition gives a = 5 and b = -1

5 xω∴ = −

2

1

B 12

dVWe know that shear force(V), dx

or V= = (5 ) 52

x = 0, F =12.5 kN (R ) so c 12.5

x = -5x + 12.52

It is clear that maximum S.F = 12.5 kN

xdx x dx x c

at

V

ω

ω

=−

− − − =− + +

=

∴ +

∫ ∫

2 2 3

2

22 3

dMFor a beam dx

5x, M = Vdx ( 5 12.5) = - 12.52 2 6

x = 0, M = 0 gives C 0

M = 12.5x - 2.5x / 6

V

x xor x dx x C

at

x

=

= − + + + + +

=

+

∫ ∫



2

2

2 3max

dMfor Maximum bending moment at 0dx

x or-5x+ 12.5 02

, 10 25 0, 5 means at centre.

So, M 12.5 2.5 2.5 5 5 / 6 20.83 kNm

or x xor x

=

+ =

− + ==

= × − × + =

A B

RA RBL

X

X

ωKNm

A

Now we consider a simply supported beam carrying uniform distributed load over whole length ( KN/m).

Here R2B

WLR

ω

= =

max

. . section X-X

212.5

x

S F atWV x

V kN

ω=+ −

=

2

x

2 2

. section X-X

M2 2

20.83 ( )2 2 2 8

( )& ( ) we get L=6.666m and =3.75kN/m

x

B M atW Wxx

dM WL L WL iidx

Solving i ii

ω

ω

=+ −

⎛ ⎞⎟⎜= − × = = −−−−⎟⎜ ⎟⎜⎝ ⎠


10mR

A RB

5KN/m 5KN/m

X

X

B-12.5KN/m 12.5KN/m

20.83KNm

Cubic parabola

S.F.D

6.666m

S.F.D

12.5kN 12.5kN

B.M.D

3.75kN/m

Parabola

20.83kNm


Chapter-4 Bending Moment and Shear Force Diagram S K Mondal’s Question: A Uniform beam of length L is carrying a uniformly distributed load w per unit

length and is simply supported at its ends. What would be the maximum bending moment and where does it occur?

Answer: By symmetry each support

reaction is equal i.e. RA=RB= 2

W

B.M at the section x-x is

Mx=+2

2 2W Wxx−

For the B.M to be maximum we

have to 0xdMdx

= that gives.

+0

2or x= i.e. at mid point.2

W xω− =

Bending Moment Diagram

And Mmax=2 2

22 2 2 8wω ω ⎡ ⎤

⎢ ⎥× − × =+⎢ ⎥⎣ ⎦

Conventional Question AMIE-1996 Question: Calculate the reactions at A and D for the beam shown in figure. Draw the bending

moment and shear force diagrams showing all important values.

Answer: Equivalent figure below shows an overhanging beam ABCDF supported by a roller support at

A and a hinged support at D. In the figure, a load of 4 kN is applied through a bracket 0.5 m away from the point C. Now apply equal and opposite load of 4 kN at C. This will be equivalent to a anticlockwise couple of the value of (4 x 0.5) = 2 kNm acting at C together with a vertical downward load of 4 kN at C. Show U.D.L. (1 kN/m) over the port AB, a point load of 2 kN vertically downward at F, and a horizontal load of 2 3 kN as shown.



For reaction and A and D.

Let ue assume RA= reaction at roller A. RDV vertically component of the reaction at the hinged support D, and

RDH horizontal component of the reaction at the hinged support D.

Obviously RDH= 2 3 kN (→ )

In order to determine RA, takings moments about D, we get

( )

A

A

A DV

2R 6 2 1 1 2 2 2 2 4 22

or R 3kNAlso R R 1 2 4 2 8

⎛ ⎞× + × = × × + + + + ×⎜ ⎟⎝ ⎠

=+ = × + + =

( ) ( ) ( )DV

222 2D DV DH

1 0

or R 5kNvetricallyupward

Reaction at D, R R R 5 2 3 6.08kN

5Inclination with horizontal tan 55.32 3

θ −

=

∴ = + = + =

= = =

( )

F

D

C

B

A

S.F.Calculation :V 2kNV 2 5 3kNV 3 4 1kNV 1kNV 1 1 2 3kN

= −= − + == − = −= −= − − × = −



( )

F

D

C

B.M.Calculation :M 0M 2 1 2kNm

M 2 1 2 5 2 2 6kNm

== − × = −

⎡ ⎤= − + + × + =⎣ ⎦

( )( )

( ) ( )

( ) ( )

− + + ×

= − + + + + − × + =

⎛ ⎞= − + + + + + + − + + − × ×⎜ ⎟⎝ ⎠

==

B

P

A

The bending moment increases from 4kNm in i,e., 2 1 2 5 2

to 6kNm as shownM 2 1 2 2 5 2 4 2 2 4kNm

2 1M 2 1 2 2 5 2 2 1 4 2 1 2 1 12 2

2.5kNmM 0

Conventional Question GATE-1997 Question: Construct the bending moment and shearing force diagrams for the beam shown in

the figure.

Answer:

Calculation: First find out reaction at B and E. Taking moments, about B, we get



[ ]

E

E

B E

B E

0.5R 4.5 20 0.5 100 50 3 40 52

or R 55kNAlso, R R 20 0.5 50 40or R 45kN R 55kN

× + × × + = × + ×

=+ = × + +

= =∵

F

E

D

B

S.F. Calculation : V 40kNV 40 55 15kNV 15 50 35kNV 35 45 10kN

= −= − + == − = −= − + =

G

F

E

D

C

B.M.Calculation : M 0M 0M 40 0.5 20kNmM 40 2 55 1.5 2.5kNm

M 40 4 55 3.5 50 2 67.5kNm

=== − × = −= − × + × =

= − × + × − × = −

B

The bending moment increases from 62.5kNm to 100.0.5M 20 0.5 2.5kNm2

−

= − × × = −

Conventional Question GATE-1996 Question: Two bars AB and BC are connected by a frictionless hinge at B. The assembly is

supported and loaded as shown in figure below. Draw the shear force and bending moment diagrams for the combined beam AC. clearly labelling the important values. Also indicate your sign convention.

Answer: There shall be a vertical reaction at hinge B and we can split the problem in two parts. Then

the FBD of each part is shown below



Calculation: Referring the FBD, we get, y 1 2F 0, and R R 200kN= + =

B 2

2

From M 0,100 2 100 3 R 4 0500or R 125kN

4

= × + × − × =

= =

∑

1

3 1

R 200 125 75kNAgain, R R 75kNand M 75 1.5 112.5kNm.

∴ = − == =

= × =

Conventional Question IES-1998 Question: A tube 40 mm outside diameter; 5 mm thick and 1.5 m long simply supported at 125

mm from each end carries a concentrated load of 1 kN at each extreme end. (i) Neglecting the weight of the tube, sketch the shearing force and bending

moment diagrams; (ii) Calculate the radius of curvature and deflection at mid-span. Take the modulus

of elasticity of the material as 208 GN/m2 Answer: (i) Given, 0 i 0d 40mm 0.04m; d d 2t 40 2 5 30mm 0.03m;= = = − = − × = =

2 2 2W 1kN; E 208GN / m 208 10 N / m ; l 1.5; a 125mm 0.125m= = = × = = =



Calculation: (ii) Radius of coordinate R As per bending equation:

( )

( )

( ) ( )

3

4 40 1

4 4 8 4

M EI y R

EIor R iM

Here,M W a 1 10 0.125 125Nm

I d d64

0.04 0.03 8.59 10 m64

σ

π

π −

= =

= − − −

= × = × × =

= −

⎡ ⎤= − = ×⎣ ⎦

( )

( )

8 8

2

x2

Substituting the values in equation i ,we get

208 10 8.59 10R 142.9m125

Deflection at mid span :

d yEI M Wx W x a Wx Wx Wa Wadx

−× × ×= =

−

= = − + − = − + − = −

1

1 1

Integrating,we getdyEI Wax Cdx

1 dyWhen, x , 02 dx

1 Wal0 Wa C or C2 2

dy WalEI Waxdx 2

= − +

= =

∴ = − + =

∴ = − +



= − + +

= =

∴ = − + +

= −

2

2

3 2

2

3 2

2

Integrating again, we getx WalEIy Wa x C2 2

When x a,y 0Wa Wa l0 C

2 2Wa Wa lor C

2 2

⎡ ⎤∴ = − + + −⎢ ⎥

⎣ ⎦⎡ ⎤

= − + + −⎢ ⎥⎣ ⎦

2 3 2

2 2

Wax Walx Wa Wa lEIy2 2 2 2

Wa x lx a alor yEI 2 2 2 2

( ) ( )2 2

2 2

2 2

9 8

At mid span,i,e., x l / 2

l / 2 l l / 2Wa a alyEI 2 2 2 2

Wa l a alEI 8 2 2

1 1000 0.125 1.5 0.125 0.125 1.58 2 2208 10 8.59 10

0.001366m 1.366mm

−

− =

⎡ ⎤×⎢ ⎥= − + + −⎢ ⎥⎣ ⎦⎡ ⎤

= − + −⎢ ⎥⎣ ⎦

⎡ ⎤× × ×= + −⎢ ⎥× × × ⎣ ⎦= =

It will be in upward direction Conventional Question IES-2001 Question: What is meant by point of contraflexure or point of inflexion in a beam? Show the

same for the beam given below:

4M 4M 2m

A C B D

20kN17.5kN/m

Answer: In a beam if the bending moment changes sign at a point, the point itself having zero bending

moment, the beam changes curvature at this point of zero bending moment and this point is called the point of contra flexure.

4M 4M 2M

A C B D

20kN17.5kN/m

BMD

From the bending moment diagram we have seen that it is between A & C. [If marks are more we should calculate exact point.]


5. Deflection of Beam

Theory at a Glance (for IES, GATE, PSU) 5.1 Introduction

• We know that the axis of a beam deflects from its initial position under action of applied forces. • In this chapter we will learn how to determine the elastic deflections of a beam.

Selection of co-ordinate axes We will not introduce any other co-ordinate system.

We use general co-ordinate axis as shown in the

figure. This system will be followed in deflection of beam and in shear force and bending moment

diagram. Here downward direction will be negative

i.e. negative Y-axis. Therefore downward deflection of

the beam will be treated as negative. To determine the value of deflection of beam

subjected to a given loading where we will use the

formula, =2

2 xd yEI Mdx

.

We use above Co-ordinate system

Some books fix a co-ordinate axis as shown in the

following figure. Here downward direction will be

positive i.e. positive Y-axis. Therefore downward

deflection of the beam will be treated as positive. As beam is generally deflected in downward directions

and this co-ordinate system treats downward

deflection is positive deflection.

To determine the value of deflection of beam

subjected to a given loading where we will use the

formula, = −2

2 xd yEI Mdx

.

Some books use above co-ordinate system

Why to calculate the deflections?

• To prevent cracking of attached brittle materials

• To make sure the structure not deflect severely and to “appear” safe for its occupants

• To help analyzing statically indeterminate structures

• Information on deformation characteristics of members is essential in the study of vibrations of machines


Chapter-5 Deflection of Beam S K Mondal’s

Several methods to compute deflections in beam • Double integration method (without the use of singularity functions)

• Macaulay’s Method (with the use of singularity functions)

• Moment area method

• Method of superposition

• Conjugate beam method

• Castigliano’s theorem

• Work/Energy methods

Each of these methods has particular advantages or disadvantages.

Assumptions in Simple Bending Theory

• Beams are initially straight

• The material is homogenous and isotropic i.e. it has a uniform composition and its mechanical

properties are the same in all directions

• The stress-strain relationship is linear and elastic

• Young’s Modulus is the same in tension as in compression

• Sections are symmetrical about the plane of bending

• Sections which are plane before bending remain plane after bending

Non-Uniform Bending

• In the case of non-uniform bending of a beam, where bending moment varies from section to section,

there will be shear force at each cross section which will induce shearing stresses

• Also these shearing stresses cause warping (or out-of plane distortion) of the cross section so that plane cross sections do not remain plane even after bending

Methods to find deflection

Double integration Geometrical Energy Method

Moment area method

Conjugate beam method

Castiglian’s theorem

Virtual Work


Chapter-5 Deflection of Beam S K Mondal’s 5.2 Elastic line or Elastic curve We have to remember that the differential equation of the elastic line is

2

2

d =Mdx x

yEI

Proof: Consider the following simply supported beam with UDL over its length.

From elementary calculus we know that curvature of a line (at point Q in figure)

2

2

3/22

2

2

d y1 dx where R radius of curvatureR dy1

dx

dyFor small deflection, 0dx

1 d yorR dx

= =⎧ ⎫⎪ ⎪⎛ ⎞+⎨ ⎬⎜ ⎟

⎝ ⎠⎪ ⎪⎩ ⎭

≈

≈



( )xx

xx

x

2x

2

2

x2

Bending stress of the beam (at point Q)M .y

EI

From strain relation we get 1 and

R EM1

R EIMd yThereforeEIdx

d yor EI Mdx

x

y

σ

ε σε

−=

= − =

∴ =

=

=

5.3 General expression

From the equation 2

2 xd yEI Mdx

= we may easily find out the following relations.

• 4

4 ω= −d yEIdx

Shear force density (Load)

• 3

3 xd yEI Vdx

= Shear force

• 2

2 xd yEI Mdx

= Bending moment

• dy = θ = slopedx

• y = δ = Deflection, Displacement • Flexural rigidity = EI

5.4 Double integration method (without the use of singularity functions)

• Vx = ω−∫ dx

• Mx = xV dx∫

• 2

2 xd yEI Mdx

=

• 1

xSlope M dxEI

θ = = ∫

• Deflection dxδ θ= = ∫

4-step procedure to solve deflection of beam problems by double integration method Step 1: Write down boundary conditions (Slope boundary conditions and displacement boundary conditions), analyze the problem to be solved

Step 2: Write governing equations for, 2

2 xd yEI Mdx

=


Chapter-5 Deflection of Beam S K Mondal’s Step 3: Solve governing equations by integration, results in expression with unknown integration constants

Step 4: Apply boundary conditions (determine integration constants)

Following table gives boundary conditions for different types of support.

Types of support and Boundary Conditions Figure Clamped or Built in support or Fixed end : ( Point A)

( )( )

, 0

, 0θ=

=

Deflection y

Slope

( ), 0 . .A finite value≠Moment M i e

Free end: (Point B)

( )( )

, 0 . .A finite value

, 0 . .A finite valueθ≠

≠

Deflection y i e

Slope i e

( ), 0=Moment M

Roller (Point B) or Pinned Support (Point A) or Hinged or Simply supported.

( ), 0=Deflection y

( ), 0 . .A finite valueθ ≠Slope i e

( ), 0=Moment M

End restrained against rotation but free to deflection

( ), 0 . .A finite value≠Deflection y i e

( ), 0θ =Slope

( ), 0=Shear force V

Flexible support

( ), 0 . .A finite value≠Deflection y i e

( ), 0 . .A finitevalueSlope i eθ ≠

( ), = rdyMoment M kdx

( ), .=Shear force V k y



Using double integration method we will find the deflection and slope of the following loaded beams one by one.

(i) A Cantilever beam with point load at the free end. (ii) A Cantilever beam with UDL (uniformly distributed load)

(iii) A Cantilever beam with an applied moment at free end. (iv) A simply supported beam with a point load at its midpoint.

(v) A simply supported beam with a point load NOT at its midpoint. (vi) A simply supported beam with UDL (Uniformly distributed load)

(vii) A simply supported beam with triangular distributed load (GVL) gradually varied load. (viii) A simply supported beam with a moment at mid span.

(ix) A simply supported beam with a continuously distributed load the intensity of which at any

point ‘x’ along the beam is sinxxw w

Lπ⎛ ⎞= ⎜ ⎟⎝ ⎠

(i) A Cantilever beam with point load at the free end. We will solve this problem by double integration method. For that at first we have to calculate (Mx).

Consider any section XX at a distance ‘x’ from free end which is left end as shown in figure.

∴ Mx = - P.x

We know that differential equation of elastic line 2

2

d yEI .dx xM P x= = −

Integrating both side we get 2

2

2

d yEI P x dxdx

dy xor EI P. A .............(i) dx 2

= −

= − +

∫ ∫



2

3

Again integrating both side we get

xEI dy = P A dx2

Pxor EIy = - Ax +B ..............(ii)6

Where A and B is integration constants.

⎛ ⎞+⎜ ⎟

⎝ ⎠

+

∫ ∫

Now apply boundary condition at fixed end which is at a distance x = L from free end and we also know that at fixed end

at x = L, y = 0

at x = L, dy 0dx

=

from equation (ii) EIL = - 3PL + AL+B ..........(iii)

6

from equation (i) EI.(0) = -2PL

2+ A …..(iv)

Solving (iii) & (iv) we get A = 2PL

2 and B = -

3PL3

Therefore, y = -3 2 3Px PL x PL

6EI 2EI 3EI+ −

The slope as well as the deflection would be maximum at free end hence putting x = 0 we get

ymax = -3PL

3EI (Negative sign indicates the deflection is downward)

(Slope)max = θ max = 2PL

2EI

Remember for a cantilever beam with a point load at free end.

Downward deflection at free end, ( )δ =3PL

3EI

And slope at free end, ( )θ =2PL

2EI


Chapter-5 Deflection of Beam S K Mondal’s (ii) A Cantilever beam with UDL (uniformly distributed load)

We will now solve this problem by double integration method, for that at first we have to calculate (Mx).

Consider any section XX at a distance ‘x’ from free end which is left end as shown in figure.

( )2

xx wxM w.x .2 2

∴ = − = −

We know that differential equation of elastic line 2 2

2

d y wxEIdx 2

= −

Integrating both sides we get 2 2

2

3

d y wxEI dx2dx

dy wxEI A ......(i)dx 6

or

= −

= − +

∫ ∫

[ ]

3

4


wxEI dy A dx6

wxor EIy = - Ax B.......(ii) 24

where A and B are integration constants

⎛ ⎞= − +⎜ ⎟

⎝ ⎠

+ +

∫ ∫

Now apply boundary condition at fixed end which is at a distance x = L from free end and we also know that at fixed end. at x = L, y = 0

at x = L, dydx

= 0

from equation (i) we get EI× (0) = 3-wL

6+ A or A =

3+wL6

from equation (ii) we get EI.y = - 4wL

24+ A.L + B

or B = - 4wL

8

The slope as well as the deflection would be maximum at the free end hence putting x = 0, we get



[ ]

( )

4

max

3

maxmax

wLy Negative sign indicates the deflection is downward8EI

wLslope6EI

θ

= −

= =

Remember: For a cantilever beam with UDL over its whole length,

Maximum deflection at free end ( )δ =4wL

8EI

Maximum slope, ( )θ =3wL

6EI

(iii) A Cantilever beam of length ‘L’ with an applied moment ‘M’ at free end.

Consider a section XX at a distance ‘x’ from free end, the bending moment at section XX is

(Mx) = -M We know that differential equation of elastic line

2

2

d yor EI M dx

= −

2

2

Integrating both side we getd yor EI M dx

dyor EI Mx + A ...(i)

dx

dx

= −

= −

∫ ∫



( )2


EI dy = M x +A dx

Mxor EI y Ax + B ...(ii) 2

Where A and B are integration constants.

= − +

∫ ∫

2 22

2 2

applying boundary conditions in equation (i) &(ii) dyat x = L, 0 gives A = MLdx

ML MLat x = L, y = 0 gives B = ML2 2

Mx MLx MLTherefore deflection equation is y = -2EI EI 2EI

Which is the

=

− = −

+ −

equation of elastic curve.

Maximum deflection at free end ∴ ( )δ2ML=

2EI (It is downward)

Maximum slope at free end ∴ ( )θ = MLEI

Let us take a funny example: A cantilever beam AB of length ‘L’ and uniform flexural rigidity EI has a bracket BA (attached to its free end. A vertical downward force P is applied to free end C of the bracket. Find the ratio a/L required in order that the deflection of point A is zero. [ISRO – 2008]

We may consider this force ‘P’ and a moment (P.a) act on free end A of the cantilever beam.



Due to point load ‘P’ at free end ‘A’ downward deflection ( )3PL

3EIδ =

Due to moment M = P.a at free end ‘A’ upward deflection ( )2 2ML (P.a)L

2EI 2EIδ = =

For zero deflection of free end A

3PL

3EI=

2(P.a)L2EI

or a 2L 3=

(iv) A simply supported beam with a point load P at its midpoint. A simply supported beam AB carries a concentrated load P at its midpoint as shown in the figure.

We want to locate the point of maximum deflection on the elastic curve and find its value. In the region 0 < x < L/2

Bending moment at any point x (According to the shown co-ordinate system)

Mx = P .x2

⎛ ⎞⎜ ⎟⎝ ⎠

and In the region L/2 < x < L

Mx = ( )P x L / 22

−

We know that differential equation of elastic line

( )2

2

d y P .x In the region 0 < x < L/22dx

EI =

Integrating both side we get

2

2

2

d y Por EI x dx 2dx

dy P xor EI . A (i) dx 2 2

=

= +

∫ ∫




[ ]

2

3

P EI dy = x A dx4

Pxor EI y = Ax + B (ii) 12

Where A and B are integrating constants

⎛ ⎞+⎜ ⎟⎝ ⎠

+

∫ ∫

Now applying boundary conditions to equation (i) and (ii) we get

2

at x = 0, y = 0dyat x = L/2, 0dx

PLA = - and B = 016

=

3 12Px PL Equation of elastic line, y = - x12 16

∴

Maximum deflection at mid span (x = L/2)( )δ3PL=

48EI

and maximum slope at each end ( )θ =2PL

16EI

(v) A simply supported beam with a point load ‘P’ NOT at its midpoint. A simply supported beam AB carries a concentrated load P as shown in the figure.

We have to locate the point of maximum deflection on the elastic curve and find the value of this deflection. Taking co-ordinate axes x and y as shown below



For the bending moment we have

In the region xP.a0 x a, M .xL

⎛ ⎞≤ ≤ = ⎜ ⎟⎝ ⎠

And, In the region a x L,≤ ≤ ( )xP.aM L - xL

= −

( )

2

2

2

2

So we obtain two differential equation for the elastic curve.d y P.aEI .x for 0 x a

Ldxd y P.aand EI . L - x for a x L

Ldx

= ≤ ≤

= − ≤ ≤

Successive integration of these equations gives 2

1

22

3

1 1

2 3

2 2

dy P.a xEI . + A ......(i) for o x adx L 2dy P.aEI P.a x - x A ......(ii) for a x Ldx L

P.a xEI y . +A x+B ......(iii) for 0 xL 6

x P.a xEI y P.a . A x + B .....(iv) for a x L2 L 6

a

= ≤ ≤

= + ≤ ≤

= ≤ ≤

= − + ≤ ≤

Where A1, A2, B1, B2 are constants of Integration. Now we have to use Boundary conditions for finding constants: BCS (a) at x = 0, y = 0 (b) at x = L, y = 0

(c) at x = a, dydx

⎛ ⎞⎜ ⎟⎝ ⎠

= Same for equation (i) & (ii)

(d) at x = a, y = same from equation (iii) & (iv)

We get ( ) ( )2 2 2 21 2

Pb P.aA L b ; A 2L a6L 6L

= − = +

31 2B 0; B Pa / 6EIand = =

Therefore we get two equations of elastic curve



( )

( ) ( )

2 2 2

3 2 2 3

PbxEI y = - L b x ..... (v) for 0 x a6L

Pb LEI y = x - a L b x - x . ...(vi) for a x L6L b

− − ≤ ≤

⎡ ⎤⎛ ⎞ + − ≤ ≤⎜ ⎟⎢ ⎥⎝ ⎠⎣ ⎦

For a > b, the maximum deflection will occur in the left portion of the span, to which equation (v) applies. Setting the derivative of this expression equal to zero gives

2 2a(a+2b) (L-b)(L+b) L bx = 3 3 3

−= =

at that point a horizontal tangent and hence the point of maximum deflection substituting this value of x

into equation (v), we find, 2 2 3/2

maxP.b(L b )y

9 3. EIL−

=

Case –I: if a = b = L/2 then

Maximum deflection will be at x =( )22L L/2

L/23

−=

i.e. at mid point

and ( )( ) ( ){ }3/222

3

max

P. L/2 L L/2 PLy48EI9 3 EIL

δ× −

= = =

(vi) A simply supported beam with UDL (Uniformly distributed load) A simply supported beam AB carries a uniformly distributed load (UDL) of intensity w/unit length over its whole span L as shown in figure. We want to develop the equation of the elastic curve and find the maximum deflection δ at the middle of the span.

Taking co-ordinate axes x and y as shown, we have for the bending moment at any point x

2

xwL xM .x - w.2 2

=

Then the differential equation of deflection becomes 2 2

x2

d y wL xEI M .x - w.2 2dx

= =

Integrating both sides we get


Chapter-5 Deflection of Beam S K Mondal’s 2 3dy wL x xEI . . A .....(i)

dx 2 2 2 3w= − +

Again Integrating both side we get 3 4wL x xEI y . . Ax + B .....(ii)

2 6 2 12w= − +

Where A and B are integration constants. To evaluate these constants we have to use boundary conditions. at x = 0, y = 0 gives B = 0

at x = L/2, 0dydx

= gives 3

24wLA = −

Therefore the equation of the elastic curve

3

3 4 3 2 3wL wL wxy . . .x = 2 . x12EI 24EI 12EI 24EI

wx x L L x⎡ ⎤= − − − +⎣ ⎦

The maximum deflection at the mid-span, we have to put x = L/2 in the equation and obtain

Maximum deflection at mid-span, ( )δ =45

384wL

EI (It is downward)

And Maximum slope A Bθ θ= at the left end A and at the right end b is same putting x = 0 or x = L

Therefore we get Maximum slope ( )θ =3

24wL

EI

(vii) A simply supported beam with triangular distributed load (GVL) gradually varied load.

A simply supported beam carries a triangular distributed load (GVL) as shown in figure below. We have to

find equation of elastic curve and find maximum deflection ( )δ .


Chapter-5 Deflection of Beam S K Mondal’s In this (GVL) condition, we get

4

4

d y wEI .x .....(i)Ldx

load= = −

Separating variables and integrating we get

( )3 2

x3

d y wxEI V + A .....(ii) 2Ldx

= = −

Again integrating thrice we get 2 3

x2

d y wxEI M + Ax +B .....(iii)6Ldx

= = −

4 2dy wx AxEI + +Bx +C .....(iv)dx 24L 2

= −

5 3 2wx Ax BxEI y + + +Cx+D .....(v)120L 6 2

= −

Where A, B, C and D are integration constant. Boundary conditions at x = 0, Mx = 0, y = 0 at x = L, Mx = 0, y = 0 gives

wLA = ,6

B = 0, 37wLC = - ,

360 D = 0

Therefore { }4 2 2 4wxy = - 7L 10L x 3x360EIL

− + (negative sign indicates downward deflection)

To find maximum deflectionδ , we have dydx

= 0

And it gives x = 0.519 L and maximum deflection ( )δ = 0.006524wL

EI

(viii) A simply supported beam with a moment at mid-span A simply supported beam AB is acted upon by a couple M applied at an intermediate point distance ‘a’ from the equation of elastic curve and deflection at point where the moment acted.

Considering equilibrium we get AMRL

= and BMRL

= −

Taking co-ordinate axes x and y as shown, we have for bending moment

In the region xM0 x a, M .xL

≤ ≤ =

In the region xMa x L, M x - ML

≤ ≤ =


Chapter-5 Deflection of Beam S K Mondal’s So we obtain the difference equation for the elastic curve

2

2

2

2

d y MEI .x for 0 x aLdx

d y Mand EI .x M for a x LLdx

= ≤ ≤

= − ≤ ≤

Successive integration of these equation gives

2

1

2

2

3

1 1

3 2

2 2

dy M xEI . A ....(i) for 0 x adx L 2dy M xEI - Mx+ A .....(ii) for a x Ldx L 2

M xand EI y = . A x + B ......(iii) for 0 x aLM x Mx EI y = A x + B ......(iv) for a x L L 2

σ

σ

= + ≤ ≤

= = ≤ ≤

+ ≤ ≤

− + ≤ ≤

Where A1, A2, B1 and B2 are integration constants.

To finding these constants boundary conditions (a) at x = 0, y = 0

(b) at x = L, y = 0

(c) at x = a, dydx

⎛ ⎞⎜ ⎟⎝ ⎠

= same form equation (i) & (ii)

(d) at x = a, y = same form equation (iii) & (iv) 2 2

1 2

2

1 2

ML Ma ML MaA M.a + + , A3 2L 3 2L

MaB 0, B2

= − = +

= =

With this value we get the equation of elastic curve

{ }

{ }

2 2 2

2 2

Mxy = - 6aL - 3a x 2L for 0 x a6L

deflection of x = a,Ma y = 3aL - 2a L

3EIL

− − ≤ ≤

∴

−

(ix) A simply supported beam with a continuously distributed load the intensity

of which at any point ‘x’ along the beam is sinxxw w

Lπ⎛ ⎞= ⎜ ⎟

⎝ ⎠

At first we have to find out the bending moment at any point ‘x’ according to the shown co-ordinate system.

We know that


Chapter-5 Deflection of Beam S K Mondal’s ( )xd V xw sindx L

π⎛ ⎞= − ⎜ ⎟⎝ ⎠

Integrating both sides we get

( )x

x

xd V w sin dx +AL

wL xor V .cos AL

π

ππ

⎛ ⎞= − ⎜ ⎟⎝ ⎠⎛ ⎞= + +⎜ ⎟⎝ ⎠

∫ ∫

and we also know that

( )xx

d M wL xV cos Adx L

ππ

⎛ ⎞= = +⎜ ⎟⎝ ⎠

Again integrating both sides we get

( )x

2

x 2

wL xd M cos A dxL

wL xor M sin Ax+BL

ππ

ππ

⎧ ⎫⎛ ⎞= +⎨ ⎬⎜ ⎟⎝ ⎠⎩ ⎭

⎛ ⎞= +⎜ ⎟⎝ ⎠

∫ ∫

Where A and B are integration constants, to find out the values of A and B. We have to use boundary

conditions at x = 0, Mx = 0

and at x = L, Mx = 0

From these we get A = B = 0. Therefore 2

x 2

wL xM sinLπ

π⎛ ⎞= ⎜ ⎟⎝ ⎠

So the differential equation of elastic curve

2 2

x2 2

d y wL xEI M sinLdxπ

π⎛ ⎞= = ⎜ ⎟⎝ ⎠

Successive integration gives

3

3

4

4

dy wL xEI cos C .......(i)dx L

wL xEIy sin Cx D .....(ii)L

ππ

ππ

⎛ ⎞= − +⎜ ⎟⎝ ⎠

⎛ ⎞= − + +⎜ ⎟⎝ ⎠

Where C and D are integration constants, to find out C and D we have to use boundary conditions at x = 0, y = 0 at x = L, y = 0

and that give C = D = 0

Therefore slope equation 3

3

dy wL xEI cosdx L

ππ

⎛ ⎞= − ⎜ ⎟⎝ ⎠

and Equation of elastic curve 4

4

wL xy sinLEIπ

π⎛ ⎞= − ⎜ ⎟⎝ ⎠

(-ive sign indicates deflection is downward)

Deflection will be maximum if xsinLπ⎛ ⎞⎜ ⎟⎝ ⎠

is maximum



xsinLπ⎛ ⎞⎜ ⎟⎝ ⎠

= 1 or x = L/2

and Maximum downward deflection ( )δ =4

4

WLEIπ

(downward).

5.5 Macaulay's Method (Use of singularity function)

• When the beam is subjected to point loads (but several loads) this is very convenient method for determining the deflection of the beam.

• In this method we will write single moment equation in such a way that it becomes continuous for

entire length of the beam in spite of the discontinuity of loading.

• After integrating this equation we will find the integration constants which are valid for entire length of the beam. This method is known as method of singularity constant.

Procedure to solve the problem by Macaulay’s method Step – I: Calculate all reactions and moments

Step – II: Write down the moment equation which is valid for all values of x. This must contain brackets.

Step – III: Integrate the moment equation by a typical manner. Integration of (x-a) will be

( )2 2x-a x not ax2 2

⎛ ⎞−⎜ ⎟

⎝ ⎠ and integration of (x-a)2 will be

( )3x-a3

so on.

Step – IV: After first integration write the first integration constant (A) after first terms and after second time integration write the second integration constant (B) after A.x . Constant A and B are valid for all

values of x. Step – V: Using Boundary condition find A and B at a point x = p if any term in Macaulay’s method, (x-a) is

negative (-ive) the term will be neglected.

(i) Let us take an example: A simply supported beam AB length 6m with a point load of 30 kN is applied at a distance 4m from left end A. Determine the equations of the elastic curve between each change of load point and the maximum deflection of the beam.

Answer: We solve this problem using Macaulay’s method, for that first writes the general momentum

equation for the last portion of beam BC of the loaded beam.

( )2

x2

d yEI M 10x -30 x - 4 .m ....(i)dx

N= =

By successive integration of this equation (using Macaulay’s integration rule

e.g ( ) ( )2x aa dx )

2x

−− =∫

We get



( ) ( )

( )

22 2

3 3 3

dyEI 5x A -15 x-4 N.m ..... iidx

5and EI y = x Ax + B - 5 (x - 4) N.m ..... iii3

= +

+

Where A and B are two integration constants. To evaluate its value we have to use following boundary

conditions. at x = 0, y = 0 and at x = 6m, y = 0

Note: When we put x = 0, x - 4 is negativre (–ive) and this term will not be considered for x = 0 , so our

equation will be EI y = 35 x Ax +B,3

+ and at x = 0 , y = 0 gives B = 0

But when we put x = 6, x-4 is positive (+ive) and this term will be considered for x = 6, y = 0 so our equation

will be EI y = 35 x3

+ Ax + 0 – 5 (x – 4)3

This gives

EI .(0) = 3 35 .6 A.6 0 5(6 4)3

+ + − −

or A = - 53 So our slope and deflection equation will be

( )

( )

22

33

dyEI 5x - 53 - 15 x - 4dx

5 and EI y x - 53x + 0 - 5 x - 43

=

=

Now we have two equations for entire section of the beam and we have to understand how we use these equations. Here if x < 4 then x – 4 is negative so this term will be deleted. That so why in the region

o x 4m≤ ≤ we will neglect (x – 4) term and our slope and deflection equation will be

2dyEI 5x -53dx

=

and 35EI y x - 53x3

=

But in the region 4 x 6mm < ≤ , (x – 4) is positive so we include this term and our slope and deflection

equation will be

( )22dyEI 5x - 53 - 15 x - 4dx

=

( )335EI y x - 53x - 5 x - 43

=

Now we have to find out maximum deflection, but we don’t know at what value of ‘x’ it will be maximum.

For this assuming the value of ‘x’ will be in the region 0 x 4m≤ ≤ .

Deflection (y) will be maximum for that dydx

= 0 or 25x - 53 = 0 or x = 3.25 m as our calculated x is in the

region 0 x 4m≤ ≤ ; at x = 3.25 m deflection will be maximum

or EI ymax = 53×3.253 – 53 ×3.25



or ymax = - 115EI

(-ive sign indicates downward deflection)

But if you have any doubt that Maximum deflection may be in the range of 4 x 6m< ≤ , use EIy = 5x2 – 53x

– 5 (x – 4)3 and find out x. The value of x will be absurd that indicates the maximum deflection will not

occur in the region 4 x 6m< ≤ .

Deflection (y) will be maximum for that dydx

= 0

or ( )225x -53 - 15 x - 4 = 0

or 10x2 -120x + 293 = 0

or x = 3.41 m or 8.6 m

Both the value fall outside the region 4 x 6m< ≤ and in this region 4 x 6m< ≤ and in this region

maximum deflection will not occur.

(ii) Now take an example where Point load, UDL and Moment applied simultaneously in a

beam: Let us consider a simply supported beam AB (see Figure) of length 3m is subjected to a point load 10 kN, UDL = 5 kN/m and a bending moment M = 25 kNm. Find the deflection of the beam at point D if flexural rigidity (EI) = 50 KNm2.

Answer: Considering equilibrium

( ) ( )A

B

B

A B A

M 0 gives

-10 1 - 25 - 5 1 1 1 1/ 2 R 3 0or R 15.83kN

R R 10 5 1 gives R 0.83kN

=

× × × + + + × =

=+ = + × = −

∑

We solve this problem using Macaulay’s method, for that first writing the general momentum equation for the last portion of beam, DB of the loaded beam.

( ) ( ) ( )= = − + −22

0x2

5 x-2d yEI M 0.83x -10 x-1 25 x-2dx 2

By successive integration of this equation (using Macaulay’s integration rule

e.g ( ) ( )2x aa dx )

2x

−− =∫

We get



( ) ( ) ( )

( ) ( ) ( )

2 32

3 2 43

dy 0.83 5EI .x A -5 x 1 25 x 2 x 2dx 2 6

0.83 5 25 5and EIy = x Ax +B - x 1 x 2 x 26 3 2 24

= − + − + − − −

− + − + − − −

Where A and B are integration constant we have to use following boundary conditions to find out A & B. at x = 0, y = 0

at x = 3m, y = 0 Therefore B = 0

3 3 2 40.83 5 5and 0 = - 3 A 3 + 0 - 2 12.5 1 16 3 24

or A = 1.93

× + × × + × − ×

( ) ( ) ( )3 2 43EIy = - 0.138x 1.93x -1.67 x 1 12.5 x 2 0.21 x 2+ − + − − −

( )( )

3 3D

D 3

Deflextion atpoint D at x = 2mEIy 0.138 2 1.93 2 1.67 1 8.85

8.85 8.85or y m ive sign indicates deflection downwardEI 50 10

0.177mm downward .

= − × + × − × = −

= − = − −×

=

(iii) A simply supported beam with a couple M at a distance ‘a’ from left end If a couple acts we have to take the distance in the bracket and this should be raised to the

power zero. i.e. M(x – a)0. Power is zero because (x – a)0 = 1 and unit of M(x – a)0 = M but we

introduced the distance which is needed for

Macaulay’s method.

( )2

0A.2

d yEI M R x M x-adx

= = −

Successive integration gives

( )

( )

21

23

dy M xEI . A - M x-adx L 2

M x-aMEI x Ax + B - 6L 2

y

= +

= +

Where A and B are integration constants, we have to use boundary conditions to find out A & B. at x = 0, y = 0 gives B = 0

at x = L, y = 0 gives A = ( )2M L-a ML 2L 6

−



8. Moment area method • This method is used generally to obtain displacement and rotation at a single point on a beam.

• The moment area method is convenient in case of beams acted upon with point loads in which case

bending moment area consist of triangle and rectangles.

• Angle between the tangents drawn at 2 points A&B on the elastic line, θ AB

θ AB =1 Area of the bending moment diagram between A&BEI

×

i.e. slope B.M.AEI

θ =AB

• Deflection of B related to 'A'

yBA = Moment of MEI

diagram between B&A taking about B (or w.r.t. B)

i.e. deflection B.MAEI ×=BA

xy

Important Note

If 1A = Area of shear force (SF) diagram

2A = Area of bending moment (BM) diagram,

Then, Change of slope over any portion of the loaded beam = 1 2A AEI×

Some typical bending moment diagram and their area (A) and distance of C.G from one edge ( )x is shown in the following table. [Note the distance will be

different from other end]

A C B

MB

Loading

B.M.diag

Deflection

L

Mn

Mc

X

θ

2θy

max

AtÎ

ABθADθ

OA

A

B

tBA

C

D


Chapter-5 Deflection of Beam S K Mondal’s Shape BM Diagram Area Distance from C.G

1. Rectangle

A bh=

2bx =

2. Triangle

=

3bx

3. Parabola

4bx =

4. Parabola

5.Cubic Parabola

6. y = k xn

7. Sine curve

Determination of Maximum slope and deflection by Moment Area- Method

(i) A Cantilever beam with a point load at free end Area of BM (Bending moment diagram)



( )

( )

( )

2

2

2

3

1 PLA L PL2 2

ThereforeA PLMaximum slope (at free end)EI 2EI

AxMaximum deflection EI

PL 2 L2 3 PL (at free end)

EI 3EI

θ

δ

= × × =

= =

=

⎛ ⎞ ⎛ ⎞×⎜ ⎟ ⎜ ⎟⎝ ⎠⎝ ⎠= =

(ii) A cantilever beam with a point load not at free end

Area of BM diagram ( )21 PaA a Pa

2 2= × × =

Therefore

( )2A PaMaximum slope

EI 2EIθ = = ( at free end)

( )2

2

AxMaximum deflection EI

Pa L-2 3 Pa . L- (at free end)

EI 2EI 3

aa

δ =

⎛ ⎞ ⎛ ⎞×⎜ ⎟ ⎜ ⎟⎝ ⎠ ⎛ ⎞⎝ ⎠= = ⎜ ⎟

⎝ ⎠

(iii) A cantilever beam with UDL over its whole length

Area of BM diagram ( ) ⎛ ⎞= × × =⎜ ⎟

⎝ ⎠

2 31 wL wLA L3 2 6

Therefore

( )3A wLMaximum slope

EI 6EIθ = = (at free end)

( ) AxMaximum deflection EI

δ =

3

4

wL 3 L6 4 wL

EI 8EI

⎛ ⎞ ⎛ ⎞×⎜ ⎟ ⎜ ⎟⎝ ⎠⎝ ⎠= = (at free end)

(iv) A simply supported beam with point load at mid-spam


Chapter-5 Deflection of Beam S K Mondal’s Area of shaded BM diagram

( )21 L PL PLA

2 2 4 16= × × =

Therefore

( )2A PLMaximum slope

EI 16EIθ = = (at each ends)


δ =

2

3

PL L16 3 PL

EI 48EI

⎛ ⎞×⎜ ⎟

⎝ ⎠= = (at mid point)

(v) A simply supported beam with UDL over its whole length Area of BM diagram (shaded)

( )2 32 L wL wLA

3 2 8 24⎛ ⎞⎛ ⎞= × × =⎜ ⎟⎜ ⎟

⎝ ⎠ ⎝ ⎠

Therefore

( )3A wLMaximum slope

EI 24EIθ = = (at each ends)


δ =

3

4

wL 5 L24 8 2 5 wL

EI 384 EI

⎛ ⎞ ⎛ ⎞× ×⎜ ⎟ ⎜ ⎟⎝ ⎠⎝ ⎠= = (at mid point)

9. Method of superposition Assumptions:

• Structure should be linear

• Slope of elastic line should be very small.

• The deflection of the beam should be small such that the effect due to the shaft or rotation of the

line of action of the load is neglected.

Principle of Superposition: • Deformations of beams subjected to combinations of loadings may be obtained as the linear

combination of the deformations from the individual loadings

• Procedure is facilitated by tables of solutions for common types of loadings and supports.

Example:

For the beam and loading shown, determine the slope and deflection at point B.


Chapter-5 Deflection of Beam S K Mondal’s Superpose the deformations due to Loading I and Loading II as shown.

10. Conjugate beam method In the conjugate beam method, the length of the conjugate beam is the same as the length of the actual beam, the loading diagram (showing the loads acting) on the conjugate beam is simply the bending-

moment diagram of the actual beam divided by the flexural rigidity EI of the actual beam, and the

corresponding support condition for the conjugate beam is given by the rules as shown below.

Corresponding support condition for the conjugate beam



Conjugates of Common Types of Real Beams Conjugate beams for statically determinate

real beams

Conjugate beams for Statically

indeterminate real beams

By the conjugate beam method, the slope and deflection of the actual beam can be found by using

the following two rules:

• The slope of the actual beam at any cross section is equal to the shearing force at the corresponding cross section of the conjugate beam.

• The deflection of the actual beam at any point is equal to the bending moment of the conjugate beam at the corresponding point.

Procedure for Analysis

• Construct the M / EI diagram for the given (real) beam subjected to the specified (real) loading. If a

combination of loading exists, you may use M-diagram by parts

• Determine the conjugate beam corresponding to the given real beam

• Apply the M / EI diagram as the load on the conjugate beam as per sign convention

• Calculate the reactions at the supports of the conjugate beam by applying equations of

equilibrium and conditions

• Determine the shears in the conjugate beam at locations where slopes is desired in the real

beam, Vconj = θreal

• Determine the bending moments in the conjugate beam at locations where deflections is desired in the real beam, Mconj = yreal


Chapter-5 Deflection of Beam S K Mondal’s The method of double integration, method of superposition, moment-area theorems, and Castigliano’s

theorem are all well established methods for finding deflections of beams, but they require that the boundary conditions of the beams be known or specified. If not, all of them become helpless. However,

the conjugate beam method is able to proceed and yield a solution for the possible deflections of the beam

based on the support conditions, rather than the boundary conditions, of the beams.

(i) A Cantilever beam with a point load ‘P’ at its free end.

For Real Beam: At a section a distance ‘x’ from free end consider the forces to the left. Taking moments about the

section gives (obviously to the left of the section) Mx = -P.x (negative sign means that the moment on the left hand side

of the portion is in the anticlockwise direction and is therefore taken as negative according to the sign convention) so that the maximum bending moment occurs at the fixed

end i.e. Mmax = - PL ( at x = L)

Considering equilibrium we get, ( )2

A AwL wLM and Reaction R3 2

= =

Considering any cross-section XX which is at a distance of x from the fixed end.

At this point load W(W ) .xLx =

Shear force ( ) = −AR area of triangle ANMxV

2

x max

x

wL 1 w wL wx- . .x .x = + - 2 2 L 2 2L

The shear force variation is parabolic.wL wLat x 0, V i.e. Maximum shear force, V2 2

at x L, V 0

⎛ ⎞= ⎜ ⎟⎝ ⎠

∴

= = + = +

= =

Bending moment ( )2

A Awx 2x= R .x - . - M2L 3xM

( )

3 2

2 2

max

x

wL wx wL= .x - - 2 6L 3

The bending moment variation is cubicwL wLat x = 0, M i.e.Maximum B.M. M .3 3

at x L, M 0

x

∴

= − = −

= =





Beam Deflection GATE-1. A lean elastic beam of given flexural

rigidity, EI, is loaded by a single force F as shown in figure. How many boundary conditions are necessary to determine the deflected centre line of the beam?

(a) 5 (b) 4 (c) 3 (d) 2

[GATE-1999] GATE-1(i) A “H” shaped frame of uniform felxural rigidity EI is loaded as shown in the figure.

The relative outward displacement between points K and O is [CE: GATE-2003]

I

J

K

M

N

OL

R R

h

h

(a) 2RL

EIh (b)

2RLEI

h

(c) 2RL

3EIh (d)

2RL3EI

h

Double Integration Method GATE-1(ii)The following statement are related to bending of beams [CE: GATE-2012] I. The slope of the bending moment diagram is equal to the shear force. II. The slope of the shear force diagram is equal to the load intensity III. The slope of the curvature is equal to the flexural rotation IV. The second derivative of the deflection is equal to the curvature. The only FALSE statement is (a) I (b) II (c) III (d) IV GATE-2. A simply supported beam carrying a concentrated load W at mid-span deflects by δ1

under the load. If the same beam carries the load W such that it is distributed


Chapter-5 Deflection of Beam S K Mondal’s uniformly over entire length and undergoes a deflection δ2 at the mid span. The ratio δ1: δ2 is: [IES-1995; GATE-1994]

(a) 2: 1 (b) 2 : 1 (c) 1: 1 (d) 1: 2 GATE-3. A simply supported laterally loaded beam was found to deflect more than a specified

value. [GATE-2003] Which of the following measures will reduce the deflection? (a) Increase the area moment of inertia (b) Increase the span of the beam (c) Select a different material having lesser modulus of elasticity (d) Magnitude of the load to be increased GATE-4. A cantilever beam of length L is subjected to a moment M at the free end. The moment of

inertia of the beam cross section about the neutral axis is I and the Young’s modulus is E. The magnitude of the maximum deflection is

2 2 2 22 4( ) ( ) ( ) ( )

2ML ML ML MLa b c d

EI EI EI EI [GATE-2012]

Statement for Linked Answer Questions GATE-5 and GATE-6:

A triangular-shaped cantilever beam of

uniform-thickness is shown in the figure.

The Young’s modulus of the material of the beam is E. A concentrated load P is applied

at the free end of the beam

t

l

P

xαα

b

[GATE-2011] GATE-5. The area moment of inertia about the neutral axis of a cross-section at a distance x

measure from the free end is

(a) 3

61bxt (b)

3

121bxt (c)

3

241bxt (d)

3

12xt

GATE-6. The maximum deflection of the beam is [GATE-2011]

(a) 33

24PlEbt

(b) 33

12PlEbt

(c) 3

38PlEbt

(d) 3

36PlEbt

GATE-7. For the linear elastic beam shown in the figure, the flexural rigidity, EI is 781250

2kN- m . When w = 10 kN/m, the vertical reaction AR at A is 50 kN. The value of AR for w = 100 kN/m is [CE: GATE-2004]


Chapter-5 Deflection of Beam S K Mondal’s w(kN/m)

B A

6 mm gap

Rigidplatform

5 m

(a) 500 kN (b) 425 kN (c) 250 kN (d) 75 kN GATE-8. Consider the beam AB shown in the figure below. Part AC of the beam is rigid while

Part CB has the flexural rigidity EI. Identify the correct combination of deflection at end B and bending moment at end A, respectively [CE: GATE-2006]

A C B

L

P

L

(a) 3PL , 2PL

3EI (b)

3PL , PL3EI

(c) 38PL , 2PL

3EI (d)

38PL , PL3EI

Statement for Linked Answer Questions 8(i) and 8(ii): In the cantilever beam PQR shown in figure below, the segment PQ has flexural rigidity EI and the segment QR has infinite flexural rigidity. [CE: GATE-2009]

R

L

W

L

P El O Rigid

GATE-8(i) The deflection and slope of the beam at Q are respectively [CE: GATE-2009]

(a) 3 25WL 3WLand

6EI 2EI (b)

3 2WL WLand3EI 2EI

(c) 3 2WL WLand

2EI EI (d)

3 2WL 3WLand3EI 2EI

GATE-8(ii) The deflection of the beam at R is [CE: GATE-2009]

(a) 38WL

EI (b)

35WL6EI

(c) 37WL

3EI (d)

38WL6EI

Common Data for Questions 9 and 10: Consider a propped cantilever beam ABC under two loads of magnitude P each as shown in the figure below. Flexural rigidity of the beam is EI. [CE: GATE-2006]



L

A

L

P

B P C a

a

GATE-9. The reaction at C is [CE: GATE-2006]

(a) 9P (upwards)16L

a (b) 9P (downwards)16L

a

(c) 9P (upwards)8L

a (d) 9P (downwards)8L

a

GATE-10. The rotation at B is [CE: GATE-2006]

(a) 5PL (clockwise)16EI

a (b) 5PL (anticlockwise)16EI

a

(c) 59PL (clockwise)16EI

a (d) 59PL (anticlockwise)16EI

a

GATE-11. The stepped cantilever is subjected to moments, M as shown in the figure below. The

vertical deflection at the free end (neglecting the self weight) is [CE: GATE-2008]

L 2

L 2

M

M

El2El

(a) 2ML

8El (b)

2ML4El

(c) 2ML

2El (d) Zero

Statement for Linked Answer Questions 12 and 13: Beam GHI is supported by three pontoons as shown in the figure below. The horizontal cross-sectional area of each pontoon is 28m , the flexural rigidity of the beam is 210000 kN- m and the

unit weight of water is 310kN/ m .

Pontoons

5 m 5 m GATE-12. When the middle pontoon is removed, the deflection at H will be (a) 0.2 m (b) 0.4 m (c) 0.6 m (d) 0.8 m [CE: GATE-2008] GATE-13. When the middle pontoon is brought back to its position as shown in the figure above, the

reaction at H will be [CE: GATE-2008] (a) 8.6 kN (b) 15.7 kN (c) 19.2 kN (d) 24.2 kN


Chapter-5 Deflection of Beam S K Mondal’s Statement for Linked Answer Questions 14 and 15: A rigid beam is hinged at one end and supported on linear elastic springs (both having a stiffness of ‘k’) at points ‘1’ and ‘2’, and an inclined load acts at ‘2’, as shown. [CE: GATE-2011]

L

√2 P

45°

45°

Hinge

Fixed

11 2

L GATE-14. Which of the following options represents the deflections 1 2andδ δ at points ‘1’ and ‘2’?

(a) 1 22 2P 4 2Pand5 5k k⎛ ⎞ ⎛ ⎞δ = δ =⎜ ⎟ ⎜ ⎟⎝ ⎠ ⎝ ⎠

(b) 1 22 P 4 Pand5 5k k⎛ ⎞ ⎛ ⎞δ = δ =⎜ ⎟ ⎜ ⎟⎝ ⎠ ⎝ ⎠

(c) 1 22 P 4 Pand5 52 2k k⎛ ⎞ ⎛ ⎞δ = δ =⎜ ⎟ ⎜ ⎟⎝ ⎠ ⎝ ⎠

(d) 1 22 2 P 4 2 Pand5 5k k⎛ ⎞ ⎛ ⎞

δ = δ =⎜ ⎟ ⎜ ⎟⎝ ⎠ ⎝ ⎠

[CE: GATE-2011] GATE-15. If the load P equals 100 kN, which of the following options represents forces 1 2R and R in the

springs at points ‘1’ and ‘2’? [CE: GATE-2011] (a) 1 2R 20kN and R 40kN= = (b) 1 2R 50kN and R 50kN= = (c) 1 2R 30kN and R 60kN= = (d) 1 2R 40kN and R 80kN= = GATE-16. The simply supported beam is subjected to a uniformly distributed load of intensity w per unit

length, on half of the span from one end. The length of the span and the flexural stiffness are denoted as l and El respectively. The deflection at mid-span of the beam is

(a) 45

6144 Ewl

l (b)

45768 E

wll

[CE: GATE-2012]

(c) 45

384 Ewl

l (d)

45192 E

wll


Double Integration Method IES-1. Consider the following statements: [IES-2003] In a cantilever subjected to a concentrated load at the free end 1. The bending stress is maximum at the free end 2. The maximum shear stress is constant along the length of the beam 3. The slope of the elastic curve is zero at the fixed end Which of these statements are correct? (a) 1, 2 and 3 (b) 2 and 3 (c) 1 and 3 (d) 1 and 2 IES-1(i). If E = elasticity modulus, I = moment of inertia about the neutral axis and M =

bending moment in pure bending under the symmetric loading of a beam, the radius of curvature of the beam: [IES-2013]

1. Increases with E 2. Increases with M 3. Decreases with I 4. Decreases with M Which of these are correct? (a) 1 and 3 (b) 2 and 3 (c) 3 and 4 (d) 1 and 4


Chapter-5 Deflection of Beam S K Mondal’s IES-2. A cantilever of length L, moment of inertia I. Young's modulus E carries a

concentrated load W at the middle of its length. The slope of cantilever at the free end is: [IES-2001]

(a) 2

2WL

EI (b)

2

4WL

EI (c)

2

8WL

EI (d)

2

16WL

EI

IES-3. The two cantilevers A

and B shown in the figure have the same uniform cross-section and the same material. Free end deflection of cantilever 'A' is δ.

[IES-2000]

The value of mid- span deflection of the cantilever ‘B’ is:

( ) ( ) ( ) ( )1 2a b c d 2 2 3δ δ δ δ

IES-4. A cantilever beam of rectangular cross-section is subjected to a load W at its free end.

If the depth of the beam is doubled and the load is halved, the deflection of the free end as compared to original deflection will be: [IES-1999]

(a) Half (b) One-eighth (c) One-sixteenth (d) Double IES-5. A simply supported beam of constant flexural rigidity and length 2L carries a

concentrated load 'P' at its mid-span and the deflection under the load isδ . If a cantilever beam of the same flexural rigidity and length 'L' is subjected to load 'P' at its free end, then the deflection at the free end will be: [IES-1998]

( ) ( ) ( ) ( )1a b c 2 d 4 2δ δ δ δ

IES-6. Two identical cantilevers are

loaded as shown in the respective figures. If slope at the free end of the cantilever in figure E is θ, the slope at free and of the cantilever in figure F will be:

Figure E Figure F [IES-1997]

(a)13θ (b)

12θ (c)

23θ (d) θ

IES-7. A cantilever beam carries a load W uniformly distributed over its entire length. If the

same load is placed at the free end of the same cantilever, then the ratio of maximum deflection in the first case to that in the second case will be:

[IES-1996] (a) 3/8 (b) 8/3 (c) 5/8 (d) 8/5 IES-8. The given figure shows a

cantilever of span 'L' subjected to a concentrated load 'P' and a moment 'M' at the free end. Deflection at the free end is given by

[IES-1996]

(a) 2 2

2 3PL MLEI EI

+ (b) 2 3

2 3ML PL

EI EI+ (c)

2 3

3 2ML PLEI EI

+ (d) 2 3

2 48ML PL

EI EI+


Chapter-5 Deflection of Beam S K Mondal’s IES-9. For a cantilever beam of length 'L', flexural rigidity EI and loaded at its free end by a

concentrated load W, match List I with List II and select the correct answer. List I List II A. Maximum bending moment 1. Wl B. Strain energy 2. Wl2/2EI C. Maximum slope 3. Wl3/3EI D. Maximum deflection 4. W2l2/6EI Codes: A B C D A B C D (a) 1 4 3 2 (b) 1 4 2 3 (c) 4 2 1 3 (d) 4 3 1 2 IES-10. Maximum deflection of a cantilever beam of length ‘l’ carrying uniformly distributed

load w per unit length will be: [IES- 2008] (a) wl4/ (EI) (b) w l4/ (4 EI) (c) w l4/ (8 EI) (d) w l4/ (384 EI)

[Where E = modulus of elasticity of beam material and I = moment of inertia of beam cross-section]

IES-11. A cantilever beam of length ‘l’ is subjected to a concentrated load P at a distance of l/3

from the free end. What is the deflection of the free end of the beam? (EI is the flexural rigidity) [IES-2004]

(a) 32

81PlEI

(b) 33

81PlEI

(c) 314

81PlEI

(d) 315

81PlEI

IES-11(i). A simply supported beam of length l is loaded by a uniformly distributed load w over

the entire span. It is propped at the mid span so that the deflection at the centre is zero. The reaction at the prop is: [IES-2013]

(a) 516

wl (b) 12

wl (c) 58

wl (d) 110

wl

IES-12. A 2 m long beam BC carries a single

concentrated load at its mid-span and is simply supported at its ends by two cantilevers AB = 1 m long and CD = 2 m long as shown in the figure.

The shear force at end A of the cantilever AB will be

(a) Zero (b) 40 kg (c) 50 kg (d) 60 kg

[IES-1997]

IES-13. Assertion (A): In a simply supported beam subjected to a concentrated load P at mid-span, the elastic curve slope becomes zero under the load. [IES-2003]

Reason (R): The deflection of the beam is maximum at mid-span. (a) Both A and R are individually true and R is the correct explanation of A (b) Both A and R are individually true but R is NOT the correct explanation of A (c) A is true but R is false (d) A is false but R is true IES-14. At a certain section at a distance 'x' from one of the supports of a simply supported

beam, the intensity of loading, bending moment and shear force arc Wx, Mx and Vx respectively. If the intensity of loading is varying continuously along the length of the beam, then the invalid relation is: [IES-2000]

( ) ( ) ( ) ( )2

2a Slope b c dx x x xx x x x

x

M dM d M dVQ V W WV dx dx dx

= = = =


Chapter-5 Deflection of Beam S K Mondal’s IES-15. The bending moment equation, as a function of distance x measured from the left

end, for a simply supported beam of span L m carrying a uniformly distributed load of intensity w N/m will be given by [IES-1999]

( ) ( ) ( ) ( ) ( ) ( )

( ) ( ) ( ) ( ) ( )

3 2

2 3 2

wL w wL wa M= L-x - L-x Nm b M= x - x Nm 2 2 2 2

wL w wL wLxc M= L-x - L-x Nm d M= x - Nm 2 2 2 2

IES-16. A simply supported beam with width 'b' and depth ’d’ carries a central load W and

undergoes deflection δ at the centre. If the width and depth are interchanged, the deflection at the centre of the beam would attain the value [IES-1997]

( ) ( ) ( ) ( )2 3 3/2

a b c d d d d db b b bδ δ δ δ⎛ ⎞ ⎛ ⎞ ⎛ ⎞

⎜ ⎟ ⎜ ⎟ ⎜ ⎟⎝ ⎠ ⎝ ⎠ ⎝ ⎠

IES-17. A simply supported beam of rectangular section 4 cm by 6 cm carries a mid-span

concentrated load such that the 6 cm side lies parallel to line of action of loading; deflection under the load is δ. If the beam is now supported with the 4 cm side parallel to line of action of loading, the deflection under the load will be:[IES-1993]

(a) 0.44 δ (b) 0.67 δ (c) 1.5 δ (d) 2.25 δ IES-18. A simply supported beam carrying a concentrated load W at mid-span deflects by δ1

under the load. If the same beam carries the load W such that it is distributed uniformly over entire length and undergoes a deflection δ2 at the mid span. The ratio δ1: δ2 is: [IES-1995; GATE-1994]

(a) 2: 1 (b) 2 : 1 (c) 1: 1 (d) 1: 2

Moment Area Method IES-19. Match List-I with List-II and select the correct answer using the codes given below

the Lists: [IES-1997] List-I List-II A. Toughness 1. Moment area method B. Endurance strength 2. Hardness C. Resistance to abrasion 3. Energy absorbed before fracture in a

tension test D. Deflection in a beam 4. Fatigue loading Code: A B C D A B C D (a) 4 3 1 2 (b) 4 3 2 1 (c) 3 4 2 1 (d) 3 4 1 2


Slope and Deflection at a Section IAS-1. Which one of the following is represented by the area of the S.F diagram from one

end upto a given location on the beam? [IAS-2004] (a) B.M. at the location (b) Load at the location (c) Slope at the location (d) Deflection at the location

Double Integration Method IAS-2. Which one of the following is the correct statement? [IAS-2007]

If for a beam 0dMdx

= for its whole length, the beam is a cantilever:

(a) Free from any load (b) Subjected to a concentrated load at its free end


Chapter-5 Deflection of Beam S K Mondal’s (c) Subjected to an end moment (d) Subjected to a udl over its whole span IAS-3. In a cantilever beam, if the length is doubled while keeping the cross-section and the

concentrated load acting at the free end the same, the deflection at the free end will increase by [IAS-1996]

(a) 2.66 times (b) 3 times (c) 6 times (d) 8 times

Conjugate Beam Method IAS-4. By conjugate beam method, the slope at any section of an actual beam is equal to:

[IAS-2002] (a) EI times the S.F. of the conjugate beam (b) EI times the B.M. of the conjugate beam (c) S.F. of conjugate beam (d) B.M. of the conjugate beam IAS-5. I = 375 × 10-6 m4; l = 0.5 m E = 200 GPa Determine the stiffness of the

beam shown in the above figure (a) 12 × 1010 N/m (b) 10 × 1010 N/m (c) 4 × 1010 N/m (d) 8 × 1010 N/m

[IES-2002]



OBJECTIVE ANSWERS

GATE-1. Ans. (d) 2

2

d yEI Mdx

= . Since it is second order differential equation so we need two boundary

conditions to solve it. GATE-1(i) Ans. (a) The bending moment in the member JN = R × h(sagging)

Slope at J or N =

Thus, outward displacement between points K and O

GATE-1(ii) Ans. (c) We know that

Also

GATE-2. Ans. (d) 3

1Wl48EI

δ = = and

43

2

W5 l5Wll

384EI 384EIδ

⎛ ⎞⎜ ⎟⎝ ⎠= = Therefore δ1: δ2 = 5: 8

GATE-3. Ans. (a) Maximum deflection (δ) = 3Wl

48EI

To reduce, δ, increase the area moment of Inertia. GATE-4. Ans. (a) GATE-5. Ans. (b) At any distance x

X-Section at x distance Area moment of inertia about

Neutral-axis of cross-section

3

3

12 121x

b t bxtlI×

= =

GATE-6. Ans. (d) From strain energy method

∴ ×R L2EIh

= × + × =2R L R L R L

2EI 2EI EIh h hh h

Wdsdx

=

M SX

dd

=

2

2EI . Md ydx

=

∴2

2MEI

d ydx

=

M EI Ry

σ= = ∴ M 1EI R

=

∴2

21R

d ydx

=

b

x

l

Ph



1 2

01 12 2 2 2 2 3 2

3 3 3 30 0

[Here, ]2

6 6 322

121

M dxU M PxEI

P x l P l P l l Px dxbxt Ebt Ebt EbtE dx

= =

= = = × =×

∫

∫ ∫

Deflection at free end

3

36U P l

P Ebtδ ∂= =

∂ GATE-7. Ans. (b) The deflection at the free end for

The gap between the beam and rigid platform is 6 mm. Hence, no reaction will be developed when w = 10 kN/m

Now, deflection at the free end for w(100 kN/m) will be = 10 × 1 mm = 10 mm But, this cannot be possible because margin of deflection is only 6m. Thus, w = 100 kN/m will induce a reaction

= Permissible deflection

GATE-8. Ans. (a) Part AC of the beam is rigid. Hence C will act as a fixed end. Thus the deflection at B will be

given as

But the bending moment does not depend on the rigidity or flexibility of the beam BM at P = P × 2L = 2PL GATE-8(i) Ans. (a) The given cantilever beam can be modified into a beam as shown below

Deflection at Q =

Slope at

GATE-8(ii) Ans. (c) Since the portion QR of the beam is rigid, QR will remain straight. Deflection of R = Deflection at Q + Slope at Q × L

× ×= = =×

4 4L 10 (5) 1000(10 kN/ m) 1mm8EI 8 781250ww

BR at B.

∴ −34

BP LL8EI 3EIw

⇒×× − =

× ×

34BR (5)100 (5) 6

8 781250 3 781250 1000

⇒×

− =×

BR 12510 61000 1000 3 781250

⇒ =BR 75 kN∴ = × − =AR (100 5 75) 425 kN

δ =3

BPL3EI

∴

P L

El WL

W

Q ×+

3 2WL WL L3EI 2EI+= =

3 3 32WL 3WL 5WL6EI 6EI

+= + = =2 2 2 2WL WL × L WL 2WL 3WLQ

2EI EI 2EI 2EI

+= + × =3 2 3 35WL 3WL 5WL 9WLL

6EI 2EI 6EI



GATE-9. Ans. (c) The moment at point B = 2 Pa In the cantilever beam ABC, the deflection at C due to meoment 2Pa will be given as

(downwards)

The reaction at C will be upwards

Thus,

GATE-10. Ans. (a) The rotation at B (i) Due to moment

(ii) Due to reaction R

GATE-11. Ans. (c) Using Moment Area Method

Deflection at B w.r.t. A = Moment of area of diagram between A and B about B

= =3 314 WL 7WL

6EI 3EI

× ⎛ ⎞δ = +⎜ ⎟⎝ ⎠

2P L LLEI 2ca

=23P L

EIa

∴δδ = =

3 3(2L) 8RL (upwards)3EI 3EIc

δ = δ′c c

=2 33P L 8RL

EI 3EIa

⇒ = 9PR (upwards)8L

a

×θ =1B

2P L (clockwise)EIa

θ = + = =2

2 2 2

BRL RL 3RL 27 P L (anti clockwise)2EI EI 2EI 16 EI

a

∴ θ = θ − θ1 2B B B

⎛ ⎞= − =⎜ ⎟⎝ ⎠

27 P L 5 P L2 (clockwise)16 EI 16 EI

a a

L 2

L 2

M M

El2El B A

2M

MEl diaghram

MEl

BMD

M +

MEl

2M L ML= LE 2 2El l

× × =


Chapter-5 Deflection of Beam S K Mondal’s GATE-12. Ans. (b) The reactions at the ends are zero as there are hinges to left of G and right of I. Hence when the

middle pontoon is removed, the beam GHI acts as a simply supported beam.

The deflection at H will be due to the load at H as well as due to the displacement of pontoons at

G and I in water. Since the loading is symmetrical, both the pontoons will be immersed to same height. Let it be x.

x × area of cross section of pontoon × unit weight of water = 24 x × 8 × 10 = 24 x = 0.3 m Also, deflection at H due to load

Final deflection at H = 0.3 + 0.1 = 0.4 m GATE-13. Ans. (c) Let the elastic deflection at H be

…(i)

The reactions at G and I will be same, as the beam is symmetrically loaded. Let the reaction at each G and I be Q. Using principle of buoyancy, we get x × area of cross-section of pontoon × x × 8 × 10 = Q

…(ii)

Also, we have Q + Q + R = P 2Q + R = 48 …(iii) Also, × area of cross-section of Pontoon = R

[from (ii)]

[from (iii)]

G H I

24 kN

48 kN

24 kN

∴⇒⇒

×= = =×

3 3

4PL 48 (10)P 0.1m

48 EI 48 10∴

δ.

∴−δ =

3(P R)L48EI

γ = Qw

⇒

⇒ = Q80

x

P

H

δ

x xx + δ

Q

R

Q

G I

⇒+ δ( )x × γw

⇒ + δ = R80

x

⇒ + δ =Q R80 80

⇒− + δ =×

48 R R2 80 80



[from (i)]

R = 19.2 kN GATE-14. Ans. (b) The free diagram of the beam is shown below.

From similar triangles, we get

…(i) Taking moments about hinge, we get [ from (i)]

From (i), we get

GATE-15. Ans. (d)

GATE-16. Ans. (b)

⇒− +δ = 2R 48 R160

⇒−δ = 3R 48

160

∴− × −=×

3

4(48 R) 10 3R 48

16048 10⇒

L

√2 P45°

L

P

P

P

RH

RVKδ1

Kδ1

δ1δ2

Kδ2

Kδ2

L L

=δ δ1 2

L 2L

⇒ δ = δ2 12

× − δ × − δ × =2 1P 2L 2L L 0k k⇒ − δ + δ =2 12P (2 ) 0k ∴⇒ − δ + δ =1 12P (4 ) 0k

⇒ δ =12P5k

δ = × =22P 4P25 5k k

×= δ = × = =1 12P 2 100R 40kN5 5

k kk

×= δ = × = =2 24P 4 100R 80kN5 5

k kk



IES IES-1. Ans. (b) IES-1(i). Ans. (d)

IES-2. Ans. (c)

2

222 8

LWWL

EI EIθ

⎛ ⎞⎟⎜ ⎟⎜ ⎟⎜⎝ ⎠= =

IES-3. Ans. (c) 3 2 3WL WL 5WLL

3EI 2EI 6EIδ

⎛ ⎞= + =⎜ ⎟

⎝ ⎠

2 3 3

midat x L

W 2Lx x 5WLyEI 2 6 6EI

δ=

⎛ ⎞= − = =⎜ ⎟

⎝ ⎠

IES-4. Ans. (c) 3 3 3

3 3

12 4Deflectionin cantilever 3 3

×= = =Wl Wl WlEI Eah Eah

( )

3 3

3 3

4 1 4If h is doubled, and W is halved, New deflection =162 2

= ×Wl WlEahEa h

IES-5. Ans. (c) ( )3 32

for simply supported beam48 6

δ = =W L WL

EI EI

3

and deflection for Cantilever 23

δ= =WLEI

IES-6. Ans. (d) When a B. M is applied at the free end of cantilever, ( ) 2/ 2

2PL LML PL

EI EI EIθ = = =

When a cantilever is subjected to a single concentrated load at free end, then 2

2PLEI

θ =

IES-7. Ans. (a) 3 3 3

8 3 8Wl WlEI EI

÷ =

IES-8. Ans. (b) IES-9. Ans. (b) IES-10. Ans. (c)

δ+

δ

δ′=

⇒ 2δ = δ′

⇒452

384 Ewl

lδ =

⇒45

768 Ewl

lδ =


Chapter-5 Deflection of Beam S K Mondal’s IES-11. Ans. (c)

( )

δ

⎛ ⎞ ⎛ ⎞ ⎛ ⎞× × × +⎜ ⎟ ⎜ ⎟ ⎜ ⎟⎝ ⎠ ⎝ ⎠ ⎝ ⎠= =

= × × =

⎛ ⎞⎜ ⎟⎧ ⎫ ⎧ ⎫⎝ ⎠= − = −⎨ ⎬ ⎨ ⎬

⎩ ⎭ ⎩ ⎭−

= × ×

=

A

3 3

2

2

max

3

3

Moment Area method gives us1 2Pl 2l l 4 l

Area 2 3 3 3 9xEI EI

Pl 2 7 14 PlEI 9 9 81 EI

2lWWa l a l 2l / 33Alternatively YEI 2 6 EI 2 6

9 2Wl 4EI 9 18

14 Wl81 EI

IES-11(i). Ans. (c) IES-12. Ans. (c) Reaction force on B and C is same 100/2 = 50 kg. And we know that shear force is same

throughout its length and equal to load at free end. IES-13. Ans. (a) IES-14. Ans. (a) IES-15. Ans. (b)

IES-16. Ans. (b) Deflection at center 3 3

3

Wl Wl48EI bd48E

12

δ = =⎛ ⎞⎜ ⎟⎝ ⎠

3 3 3 2 2

2 23 3In second case,deflection

4848 48

12 12

δ δ′= = = = =′ ⎛ ⎞ ⎛ ⎞

⎜ ⎟ ⎜ ⎟⎝ ⎠ ⎝ ⎠

Wl Wl Wl d dEI b bdb bdE E

IES-17. Ans. (d) Use above explanation

IES-18. Ans. (d) 3

1Wl48EI

δ = = and

43

2

W5 l5Wll

384EI 384EIδ

⎛ ⎞⎜ ⎟⎝ ⎠= = Therefore δ1: δ2 = 8: 5

IES-19. Ans. (c)

IAS IAS-1. Ans. (a) IAS-2. Ans. (c) udl or point load both vary with x. But

if we apply Bending Moment (M) = const.

and 0dMdx

=

IAS-3. Ans. (d)

33

3 2 2

1 1

LPL L 83EI L

δδ δδ

⎛ ⎞= ∴ ∞ ∴ = =⎜ ⎟

⎝ ⎠

IAS-4. Ans. (c)


Chapter-5 Deflection of Beam S K Mondal’s IAS-5. Ans. (c) Stiffness means required load for unit deformation. BMD of the given beam

Loading diagram of conjugate beam

The deflection at the free end of the actual beam = BM of the at fixed point of conjugate beam

31 2 1 2 3

2 3 2 2 2 2 3 2ML L WL L WL L WLy L L L L LEI EI EI EI

⎛ ⎞ ⎛ ⎞ ⎛ ⎞ ⎛ ⎞ ⎛ ⎞⎟ ⎟ ⎟ ⎟ ⎟⎜ ⎜ ⎜ ⎜ ⎜= × × × + × × + + × × × + =⎟ ⎟ ⎟ ⎟ ⎟⎜ ⎜ ⎜ ⎜ ⎜⎟ ⎟ ⎟ ⎟ ⎟⎜ ⎜ ⎜ ⎜ ⎜⎝ ⎠ ⎝ ⎠ ⎝ ⎠ ⎝ ⎠ ⎝ ⎠

Or stiffness = ( ) ( )

( )

9 610

3 3

2 200 10 375 102 4 10 /3 3 0.5

W EI N my L

−× × × ×= = = ×

×


Conventional Question GATE-1999 Question: Consider the signboard mounting shown in figure below. The wind load acting

perpendicular to the plane of the figure is F = 100 N. We wish to limit the deflection, due to bending, at point A of the hollow cylindrical pole of outer diameter 150 mm to 5 mm. Find the wall thickness for the pole. [Assume E = 2.0 X 1011 N/m2]

Answer: Given: F = 100 N; d0 = 150 mm, 0.15 my = 5 mm; E = 2.0 X 1O11 N/m2 Thickness of pole, t The system of signboard mounting can be considered as a cantilever loaded at A i.e. W = 100

N and also having anticlockwise moment of M = 100 x 1 = 100 Nm at the free end. Deflection of cantilever having concentrated load at the free end,

3 2

3 33

11 11

3 36 4

3 11 11

WL MLy3EI 2EI

100 5 100 55 103 2.0 10 I 2 2.0 10 I

1 100 5 100 5or I 5.417 10 m5 10 3 2.0 10 2 2.0 10

−

−−

= +

× ×× = +× × × × × ×⎡ ⎤× ×= + = ×⎢ ⎥× × × × ×⎣ ⎦



( )

( )

4 40 i

6 4 4i

But I d d64

5.417 10 0.15 d64

π

π−

= −

∴ × = −

i

0 i

or d 0.141m or 141 mmd d 150 141t 4.5mm

2 2

=− −∴ = = =

Conventional Question IES-2003 Question: Find the slope and deflection at the free end of a cantilever beam of length 6m as

loaded shown in figure below, using method of superposition. Evaluate their numerical value using E = 200 GPa, I = 1×10-4 m4 and W = 1 kN.

Answer: We have to use superposition theory.

1st consider

δ

θ

33

2 2

(3 ) 2 83 3

(3 ).2 62 2

c

c

WPL WEI EI EI

PL W WEI EI EI

×= = =

= = =

δ δ1 c8W 6 32 at A due to this load( ) = .(6 2) = 4EIc

W WDeflectionEI EI

θ+ − + × =

( )

2

δ

δ

δ

nd

3

B

2

2 consider:2 4 128

3 3(2 ) 4 16

2 at A due to this load( )

224W = (6 4)=3EI

B

B B

W WEI EI

W WEI EI

Deflection

θ

θ

×= =

×= =

+ × −

.

δ δ3

3

2

A

6 72( )3

6 18 2

rd3 consider :

AW W

EI EIW W

EI EIθ

×= = =

×= =

( )( )

( )

1

θ θ θ θ

δ δ δ δ

3

A 9 4

2 3

3

9 4

Apply superpositioning form ula

40 106 16 18 40=200 10 10

32 224 72 40 563×W=3 3EI

563×(10 ) = 8.93 m m3 (200 10 ) 10

B cW W W WEI EI EI EI

W W W WEI EI EI EI

−

−

×+ + = + + = =

× ×

= + + = + + =

=× × ×

Conventional Question IES-2002 Question: If two cantilever beams of identical dimensions but made of mild steel and grey cast

iron are subjected to same point load at the free end, within elastic limit, which one will deflect more and why?


Chapter-5 Deflection of Beam S K Mondal’s Answer: Grey cost iron will deflect more.

We know that a cantilever beam of length 'L' end load 'P' will deflect at free end

(δ ) = 3

3PLEI

Mild steel

1

125 and E 200 Cast Iron

EE GPa GPa

δ∴ ∝

Conventional Question IES-1997 Question: A uniform cantilever beam (EI = constant) of length L is carrying a concentrated

load P at its free end. What would be its slope at the (i) Free end and (ii) Built in end

Answer: (i) Free end, θ=2PL

2EI

(ii) Built-in end, θ 0=

L

P


6. Bending Stress in Beam

Theory at a Glance (for IES, GATE, PSU) 6.1 Euler Bernoulli’s Equation or (Bending stress formula) or Bending Equation

σ = =M Ey I R

Where σ = Bending Stress

M = Bending Moment

I = Moment of Inertia E = Modulus of elasticity R = Radius of curvature y = Distance of the fibre from NA (Neutral axis)

6.2 Assumptions in Simple Bending Theory All of the foregoing theory has been developed for the case of pure bending i.e. constant B.M along the length of the beam. In such case

• The shear force at each c/s is zero.

• Normal stress due to bending is only produced.

• Beams are initially straight

• The material is homogenous and isotropic i.e. it has a uniform composition and its mechanical properties are the same in all directions

• The stress-strain relationship is linear and elastic

• Young’s Modulus is the same in tension as in compression

• Sections are symmetrical about the plane of bending

• Sections which are plane before bending remain plane after bending

6.3


Chapter-6 Bending Stress in Beam S K Mondal’s

1maxσ σ= =t

McI

2minσ σ= =c

McI

(Minimum in sense of sign)

6.4 Section Modulus (Z)

IZ = y

• Z is a function of beam c/s only

• Z is other name of the strength of the beam

• The strength of the beam sections depends mainly on the section modulus

• The flexural formula may be written as, σ = MZ

• Rectangular c/s of width is "b" & depth "h" with sides horizontal, Z = 2

6bh

• Square beam with sides horizontal, Z = 3

6a

• Square c/s with diagonal horizontal, Z = 3

6 2a

• Circular c/s of diameter "d", Z = 3

32dπ

A log diameter "d" is available. It is proposed to cut out a strongest beam from it. Then

Z = 2 2( )6

b d b−

Therefore, Zmax = 3 dfor b =

9 3bd

6.5 Flexural Rigidity (EI) Reflects both

• Stiffness of the material (measured by E) • Proportions of the c/s area (measured by I )

6.6 Axial Rigidity = EA

6.7 Beam of uniform strength It is one is which the maximum bending stress is same in every section along the longitudinal axis.


Chapter-6 Bending Stress in Beam S K Mondal’s For it 2 bhM α Where b = Width of beam h = Height of beam

To make Beam of uniform strength the section of the beam may be varied by • Keeping the width constant throughout the length and varying the depth, (Most widely used) • Keeping the depth constant throughout the length and varying the width • By varying both width and depth suitably.

6.8 Bending stress due to additional Axial thrust (P). A shaft may be subjected to a combined bending and axial thrust. This type of situation arises in various machine elements.

If P = Axial thrust

Then direct stress ( dσ ) = P / A (stress due to axial thrust)

This direct stress ( dσ ) may be tensile or compressive depending upon the load P is tensile or compressive.

And the bending stress ( bσ ) = MyI

is varying linearly from zero at centre and extremum (minimum or

maximum) at top and bottom fibres.

If P is compressive then

• At top fibre P MyA I

σ = + (compressive)

• At mid fibre PA

σ = (compressive)

• At bottom fibre PA

σ = – MyI

(compressive)

6.9 Load acting eccentrically to one axis

• ( )

maxσ×

= +P e yP

A I where ‘e’ is the eccentricity at which ‘P’ is act.

• ( )

minσ×

= −P e yP

A I


Chapter-6 Bending Stress in Beam S K Mondal’s Condition for No tension in any section

• For no tension in any section, the eccentricity must not exceed 22k

d

[Where d = depth of the section; k = radius of gyration of c/s]

• For rectangular section (b x h) , 6he ≤ i.e load will be 2

3he = of the middle section.

• For circular section of diameter ‘d’ , 8de ≤ i.e. diameter of the kernel, 2

4de =

For hollow circular section of diameter ‘d’ , 2 2

8D de

D+≤ i.e. diameter of the kernel, +≤

2 2

2 .4

D deD





Bending equation GATE-1. A cantilever beam has the

square cross section 10mm × 10 mm. It carries a transverse load of 10 N. Considering only the bottom fibres of the beam, the correct representation of the longitudinal variation of the bending stress is: [GATE-2005]

GATE-1(i) A homogeneous, simply supported prismatic beam of width B, depth D and span L is

subjected to a concentrated load of magnitude P. The load can be placed anywhere along the span of the beam. The maximum flexural stress developed in beam is

(a) 22 PL3 BD

(b) 23 PL4 BD

[CE: GATE-2004]

(c) 24 PL3 BD

(d) 23 PL2 BD

GATE-1(ii) Consider a simply supported beam with a uniformly distributed load having a

neutral axis (NA) as shown. For points P (on the neutral axis) and Q(at the bottom of the beam) the state of stress is best represented by which of the following pairs?

Q P

NA

L L [CE: GATE-2011] (a) (b)

P Q

P Q

(c) (d)



P Q

P Q

GATE-2. Two beams, one having square cross section and another circular cross-section, are

subjected to the same amount of bending moment. If the cross sectional area as well as the material of both the beams are the same then [GATE-2003]

(a) Maximum bending stress developed in both the beams is the same (b) The circular beam experiences more bending stress than the square one (c) The square beam experiences more bending stress than the circular one (d) As the material is same both the beams will experience same deformation GATE-2(i) A beam with the cross-section given below is subjected to a positive bending

moment(causing compression at the top) of 16 kN-m acting around the horizontal axis. The tensile force acting on the hatched area of the cross-section is

50 mm 50 mm

50 mm

25 mm

75 mm

[CE: GATE-2006] (a) zero (b) 5.9 kN (c) 8.9 kN (d) 17.8 kN

Section Modulus GATE-3. Match the items in Columns I and II. [GATE-2006] Column-I Column-II P. Addendum 1. Cam Q. Instantaneous centre of velocity 2. Beam R. Section modulus 3. Linkage S. Prime circle 4. Gear (a) P – 4, Q – 2, R – 3, S – l (b) P – 4, Q – 3, R – 2, S – 1 (c) P – 3, Q – 2, R – 1, S – 4 (d) P – 3, Q – 4, R – 1, S – 2

Combined direct and bending stress GATE-4. For the component loaded with a force F as shown in the figure, the axial stress at

the corner point P is: [GATE-2008]



(a) 34)3(

bbLF −

(b) 34)3(

bbLF +

(c) 34)43(

bbLF −

(d) 34)23(

bbLF −

GATE-5. A simply supported beam of uniform rectangular cross-section of width b and depth h

is subjected to linear temperature gradient, 0º at the top and Tº at the bottom, as shown in the figure. The coefficient of linear expansion of the beam material is .α The resulting vertical deflection at the mid-span of the beam is [CE: GATE-2003]

L

0°

T°Temp. Gradient

(a) 2T upward

8Lhα (b)

2TL upward8h

α

(c) 2T downward

8Lhα (d)

2TL downward8h

α

GATE-6. The maximum tensile stress at the section X-X shown in the figure below is

L 2

L 2

L3

L3

L 3

X

X

d/2d/2

b

d

(a) 8P

bd (b) 6P

bd [CE: GATE-2008]

(c) 4Pbd

(d) 2Pbd


Bending equation IES-1. Beam A is simply supported at its ends and carries udl of intensity w over its entire

length. It is made of steel having Young's modulus E. Beam B is cantilever and carries a udl of intensity w/4 over its entire length. It is made of brass having Young's modulus E/2. The two beams are of same length and have same cross-sectional area. If σA and σB denote the maximum bending stresses developed in beams A and B, respectively, then which one of the following is correct? [IES-2005]

(a) σA/σB (b) σA/σB < 1.0 (c) σA/σB > 1.0 (d) σA/σB depends on the shape of cross-section IES-2. If the area of cross-section of a circular section beam is made four times, keeping the

loads, length, support conditions and material of the beam unchanged, then the qualities (List-I) will change through different factors (List-II). Match the List-I with the List-II and select the correct answer using the code given below the Lists:[IES-2005]

List-I List-II


Chapter-6 Bending Stress in Beam S K Mondal’s A. Maximum BM 1. 8 B. Deflection 2. 1 C. Bending Stress 3. 1/8 D. Section Modulus 4. 1/16 Codes: A B C D A B C D (a) 3 1 2 4 (b) 2 4 3 1 (c) 3 4 2 1 (d) 2 1 3 4 IES-3. Consider the following statements in case of beams: [IES-2002] 1. Rate of change of shear force is equal to the rate of loading at a particular

section 2. Rate of change of bending moment is equal to the shear force at a particular

suction. 3. Maximum shear force in a beam occurs at a point where bending moment is

either zero or bending moment changes sign Which of the above statements are correct? (a) 1 alone (b) 2 alone (c) 1 and 2 (d) 1, 2 and 3 IES-4. Match List-I with List-II and select the correct answer using the code given below the

Lists: [IES-2006] List-I (State of Stress) List-II (Kind of Loading)

1. Combined bending and torsion of circular shaft

2. Torsion of circular shaft

3. Thin cylinder subjected to internal pressure

4. Tie bar subjected to tensile force

Codes: A B C D A B C D (a) 2 1 3 4 (b) 3 4 2 1 (c) 2 4 3 1 (d) 3 1 2 4 IES-4a. A T-section beam is simply supported and subjected to a uniform distributed load

over its whole span. Maximum longitudinal stress at [IES-2011] (a) Top fibre of the flange (b) The junction of web and flange (c) The mid-section of the web (d) The bottom fibre of the web

IES-4b. A rotating shaft carrying a unidirectional transverse load is subjected to: (a) Variable bending stress (b) Variable shear stress [IES-2013] (c) Constant bending stress (d) Constant shear stress IES-4c. Statement (I): A circular cross section column with diameter ‘d’ is to be axially loaded

in compression. For this the core of the section is considered to be a concentric

circulation area of diameter ' '.4d [IES-2013]


Chapter-6 Bending Stress in Beam S K Mondal’s Statement (II): We can drill and take out a cylindrical volume of material with

diameter ' '4d in order to make the column lighter and still maintaining the same

buckling (crippling) load carrying capacity. (a) Both Statement (I) and Statement (II) are individually true and Statement (II) is the correct

explanation of Statement (I) (b) Both Statement (I) and Statement (II) are individually true but Statement (II) is not the

correct explanation of Statement (I) (c) Statement (I) is true but Statement (II) is false (d) Statement (I) is false but Statement (II) is true

Section Modulus IES-5. Two beams of equal cross-sectional area are subjected to equal bending moment. If

one beam has square cross-section and the other has circular section, then[IES-1999] (a) Both beams will be equally strong (b) Circular section beam will be stronger (c) Square section beam will be stronger (d) The strength of the beam will depend on the nature of loading IES-6. A beam cross-section is used in

two different orientations as shown in the given figure:

Bending moments applied to the beam in both cases are same. The maximum bending stresses induced in cases (A) and (B) are related as:

(a) 4A Bσ σ= (b) 2A Bσ σ=

(c) 2

BA

σσ = (d) 4

BA

σσ = A B

[IES-1997] IES-6(i). A beam with a rectangular section of 120 mm × 60 mm, designed to be placed

vertically is placed horizontally by mistake. If the maximum stress is to be limited, the reduction in load carrying capacity would be [IES-2012] 14 13 12 16

IES-7. A horizontal beam with square cross-section is simply supported with sides of the

square horizontal and vertical and carries a distributed loading that produces maximum bending stress σ in the beam. When the beam is placed with one of the diagonals horizontal the maximum bending stress will be:

[IES-1993]

1(a) (b) (c) 2 (d) 22σ σ σ σ

IES-7(i). The ratio of the moments of resistance of a square beam (Z) when square section is placed (i) with two sides horizontal (Z1) and (ii) with a diagonal horizontal (Z2 ) as shown is [IES-2012] = . = . = √ = .



IES-8. Which one of the following combinations of angles will carry the maximum load as a

column? [IES-1994]

IES-9. Assertion (A): For structures steel I-beams preferred to other shapes. [IES-1992] Reason (R): In I-beams a large portion of their cross-section is located far from the

neutral axis. (a) Both A and R are individually true and R is the correct explanation of A (b) Both A and R are individually true but R is NOT the correct explanation of A (c) A is true but R is false (d) A is false but R is true

Combined direct and bending stress IES-10. Assertion (A): A column subjected to eccentric load will have its stress at centroid

independent of the eccentricity. [IES-1994] Reason (R): Eccentric loads in columns produce torsion. (a) Both A and R are individually true and R is the correct explanation of A (b) Both A and R are individually true but R is NOT the correct explanation of A (c) A is true but R is false (d) A is false but R is true IES-11. For the configuration of loading shown in the given figure, the stress in fibre AB is

given by: [IES-1995]

(a) P/A (tensile) (b) . .5

xx

P P eA I

⎛ ⎞−⎜ ⎟

⎝ ⎠(Compressive)

(c) . .5

xx

P P eA I

⎛ ⎞+⎜ ⎟

⎝ ⎠(Compressive) (d) P/A (Compressive)



IES-12. A column of square section 40 mm × 40

mm, fixed to the ground carries an eccentric load P of 1600 N as shown in the figure.

If the stress developed along the edge CD is –1.2 N/mm2, the stress along the edge AB will be:

(a) –1.2 N/mm2 (b) +1 N/mm2 (c) +0.8 N/mm2 (d) –0.8 N/mm2

[IES-1999]

IES-13. A short column of symmetric cross-

section made of a brittle material is subjected to an eccentric vertical load P at an eccentricity e. To avoid tensile stress in the short column, the eccentricity e should be less than or equal to:

(a) h/12 (b) h/6 (c) h/3 (d) h/2

[IES-2001]

IES-14. A short column of external diameter D and internal diameter d carries an eccentric load W. Toe greatest eccentricity which the load can have without producing tension on the cross-section of the column would be: [IES-1999]

2 2 2 2 2 2

(a) (b) (c) (d)8 8 8 8+ + + +D d D d D d D d

d D


Chapter-6 Bending Stress in Beam S K Mondal’s IES-15 The ratio of the core of a rectangular section to the area of the rectangular section

when used as a short column is [IES-2010]

(a) 19

(b) 136

(c) 1

18 (d) 1

24


Bending equation IAS-1. Consider the cantilever loaded as shown below: [IAS-2004]

What is the ratio of the maximum compressive to the maximum tensile stress? (a) 1.0 (b) 2.0 (c) 2.5 (d) 3.0 IAS-2. A 0.2 mm thick tape goes over a frictionless pulley of 25 mm diameter. If E of the

material is 100 GPa, then the maximum stress induced in the tape is: [IAS 1994] (a) 100 MPa (b) 200 MPa (c) 400 MPa (d) 800 MPa

Section Modulus IAS-3. A pipe of external diameter 3 cm and internal diameter 2 cm and of length 4 m is

supported at its ends. It carries a point load of 65 N at its centre. The sectional modulus of the pipe will be: [IAS-2002]

(a) 36564

cmπ (b) 365

32cmπ

(c) 36596

cmπ (d) 365

128cmπ

IAS-4. A Cantilever beam of rectangular cross-section is 1m deep and 0.6 m thick. If the

beam were to be 0.6 m deep and 1m thick, then the beam would. [IAS-1999] (a) Be weakened 0.5 times (b) Be weakened 0.6 times


Chapter-6 Bending Stress in Beam S K Mondal’s (c) Be strengthened 0.6 times (d) Have the same strength as the original beam because the cross-sectional area remains the

same IAS-5. A T-beam shown in the given figure is

subjected to a bending moment such that plastic hinge forms. The distance of the neutral axis from D is (all dimensions are in mm)

(a) Zero (b) 109 mm (c) 125 mm (d) 170 mm

[IAS-2001]

IAS-6. Assertion (A): I, T and channel sections are preferred for beams. [IAS-2000] Reason(R): A beam cross-section should be such that the greatest possible amount of

area is as far away from the neutral axis as possible. (a) Both A and R are individually true and R is the correct explanation of A (b) Both A and R are individually true but R is NOT the correct explanation of A (c) A is true but R is false (d) A is false but R is true IAS-7. If the T-beam cross-section

shown in the given figure has bending stress of 30 MPa in the top fiber, then the stress in the bottom fiber would be (G is centroid)

(a) Zero (b) 30 MPa (c) –80 MPa (d) 50 Mpa

[IAS-2000]

IAS-8. Assertion (A): A square section is more economical in bending than the circular section of same area of cross-section. [IAS-1999]

Reason (R): The modulus of the square section is less than of circular section of same area of cross-section.


Bimetallic Strip IAS-9. A straight bimetallic strip of copper and steel is heated. It is free at ends. The strip,

will: [IAS-2002] (a) Expand and remain straight (b) Will not expand but will bend (c) Will expand and bend also (d) Twist only


Chapter-6 Bending Stress in Beam S K Mondal’s Combined direct and bending stress IAS-10. A short vertical column having a

square cross-section is subjected to an axial compressive force, centre of pressure of which passes through point R as shown in the above figure. Maximum compressive stress occurs at point

(a) S (b) Q (c) R (d) P

[IAS-2002]

IAS-11. A strut's cross-sectional area A is subjected to load P a point S (h, k) as shown in the given figure. The stress at the point Q (x, y) is: [IAS-2000]

(a) x y

P Phy PkxA I I+ +

(b) y x

P Phx PkyA I I

− − −

(c) y x

P Phy PkxA I I+ +

(d) y x

P Phx PkyA I I+ −

OBJECTIVE ANSWERS

GATE-1. Ans. (a) ( )( )x 4

10 x 0.005M MyM P.x or 60.(x) MPaI y I 0.01

12

σ σ× ×

= = = = =

At x 0; 0At x 1m; 60MPa

σσ

= == =

And it is linear as xσ ∞ GATE-1(i) Ans. (d) When the concentrated load is placed at the midspan, maximum bending moment will develop

at the mid span.

Now,

GATE-1(ii) Ans. (a) There can be two stresses which can act at any point on the beam viz. flexural stress and shear

stress.

Where all the symbols have their usual meaning.

MI

yσ = ⎡ ⎤=⎢ ⎥⎣ ⎦∵ PLM

4

×= =3 2

PL D3PL4 2

BD 2BD12

maxMI

yσ = ×

τ = SAI

yb



GATE-2. Ans. (b) M E My; or ;I y I

σ σρ

= = =

2

2sq cir3 4 3 3 3

3

a dM M6M 32M 4 M 22.27M d2 2; a

1 4a d d a aa.a12 64

π π πσ σπ π

⎛ ⎞ ⎛ ⎞⎜ ⎟ ⎜ ⎟ ⎡ ⎤⎝ ⎠ ⎝ ⎠= = = = = = =⎢ ⎥

⎣ ⎦∵

sq cirσ σ∴ < GATE-2(i) Ans. (c)

From similar traingles, we have

Tensile force =

GATE-3. Ans. (b) GATE-4. Ans. (d) Total Stress = Direct stress + Stress due to Moment =

2 3

( )4 2 ( )

12

P My F F L b bA I b b b

− ×+ = +

×

GATE-5. Ans. (d)

The average change in temperature =

The compression in the top most fibre =

Similarly, the elongation in bottom most fibre

Strain,

Therefore deflection at midpoint is downward. Now, from the equation of pure bending, we have

Curvature,

100 mm 50 mm

50 mm

25 mm

75 mm

x

Bending stress distribution

fmax

= ×max maxMI

f y

× ×= × =×

62

316 10 12 75 42.67 N/ mm100 150

=42.6775 25

x

⇒ = 214.22 N/ mmx

∴ −× × × × = =31 25 14.22 50 10 8.88 8.9 kN2

T2

α × × TL2

α × × TL2

∴ α αε = =×0

L T TL 2 2

M EI R y

σ= =

⇒1R E y

σ=

= Strainy

⎡ ⎤=⎢ ⎥⎣ ⎦∵

2hy



Also, from the property of circle, we have

Deflection,

GATE-6. Ans. (a) The section at X – X may be shown as in the figure below:

The maximum tensile stress at the section X – X is

IES

IES-1. Ans. (d) Bending stress ( ) My , y and I both depends on theI

σ =

A

B

Shape of cross sec tion so depends on the shape of cross sec tionσσ

− −

IES-2. Ans. (b) Diameter will be double, D = 2d. A. Maximum BM will be unaffected

B. deflection ratio 4

1

2

EI d 1EI 4 16

⎛ ⎞= =⎜ ⎟⎝ ⎠

C. Bending stress ( ) 32

41

M d / 2My d 1or Bending stress ratioI D 8d

64

σσσπ

⎛ ⎞= = = = =⎜ ⎟⎝ ⎠

D. Selection Modulus ratio3

2 2 1

1 1 1

Z I y D 8Z y I d

⎛ ⎞= = × = =⎜ ⎟⎝ ⎠

IES-3. Ans. (c) IES-4. Ans. (c) IES-4a. Ans. (d) IES-4b. Ans. (a) IES-4c. Ans. (c)

IES-5. Ans. (b) If D is diameter of circle and 'a' the side of square section, 2 2 44

d a or d aππ

= =

Z for circular section = 2 3 3

; and Z for square section =32 64d a aπ

π=

ε α= =02 Th h

δ =2L

8Rα α= × =

2 2L T TL downward8 8h h

d2

d4

P b

σ = +P MA Z

⎛ ⎞× ×⎜ ⎟⎝ ⎠= + = + =

⎛ ⎞ ⎛ ⎞× ×⎜ ⎟ ⎜ ⎟⎝ ⎠ ⎝ ⎠

2

P 6P 2P 6P 8P4

2 4

d

d bd bd bddb b



IES-6. Ans. (b) Z for rectangular section is 2

6bd

,

2

23 32 2,

6 24 6 12

⎛ ⎞×⎜ ⎟

⎝ ⎠= = = =A B

b bb bb bZ Z

3 3

. . , 224 12

= = = =σ σ σ σ σ σA A B B A B A Bb bM Z Z or or

IES-6(i). Ans. (c)

IES-7. Ans. (c) Bending stress = MZ

For rectangular beam with sides horizontal and vertical, Z = 3

6a

For same section with diagonal horizontal, Z =3

6 2a

∴ Ratio of two stresses = 2 IES-7(i). Ans. (c) IES-8. Ans. (a) IES-9. Ans. (a) IES-10. Ans. (c) A is true and R is false.

IES-11. Ans. (b) (compressive), (tensile)σ σ= = =d xx x

P My PkyA I I

IES-12. Ans. (d) Compressive stress at CD = 1.2 N/mm2 = 6 1600 61 1

1600 20⎛ ⎞ ⎛ ⎞+ = +⎜ ⎟ ⎜ ⎟⎝ ⎠ ⎝ ⎠

P e eA b

( ) 26 1600or 0.2. Sostressat 1 0.2 0.8 N/mm (com)20 1600

= = − − = −e AB

IES-13. Ans. (b) IES-14. Ans. (c)

IES-15 Ans. (c) 1 42 6 6 18

b h bhA = × × × =

IAS

IAS-1. Ans. (b) σ= compressive, Max2 at lower end of A.3

σ ⎛ ⎞= ×⎜ ⎟⎝ ⎠

My M hI I

σ tensile, max = at upper end of3

⎛ ⎞× ⎜ ⎟⎝ ⎠

M h BI

IAS-2. Ans. (d) RE

y=σ

Here y = 1.022.0 = mm = 0.1 x 10-3 m, R =

225

mm = 12.5 x 10-3 m

or 3

33

105.12101.010100

−

−

××××=σ MPa = 800MPa

IAS-3. Ans. (c) ( )4 4

33 2

64Section modulus (z) cm32

Iy

π −= = = 365

96cmπ



IAS-4. Ans. (b) ×= = =3

31

I 0.6 1z 1.2my 0.5

×= = =3

32

I 1 0.6and z 0.72my 0.3

2

1

z 0.72 0.6 timesz 1.2

∴ = =

IAS-5. Ans. (b)

IAS-6. Ans. (a) Because it will increase area moment of inertia, i.e. strength of the beam.

IAS-7. Ans. (c) ( )1 1

1 2 12 2

2

30110 30 8030

M or y MPaI y y y

σ σ σσ= = = × = − × =

As top fibre in tension so bottom fibre will be in compression. IAS-8. ans. (c) IAS-9. Ans. (c) As expansion of copper will be more than steel. IAS-10. Ans. (a) As direct and bending both the stress is compressive here. IAS-11. Ans. (b) All stress are compressive, direct stress,

(compressive), (compressive)σ σ= = =d xx x

P My PkyA I I

and (compressive)σ = =yy y

Mx PhxI I




Conventional Question IES-2008 Question: A Simply supported beam AB of span length 4 m supports a uniformly distributed

load of intensity q = 4 kN/m spread over the entire span and a concentrated load P = 2 kN placed at a distance of 1.5 m from left end A. The beam is constructed of a rectangular cross-section with width b = 10 cm and depth d = 20 cm. Determine the maximum tensile and compressive stresses developed in the beam to bending.

Answer:

A BR + R = 2 + 4×4.........(i)

A-R ×4 + 2×(4-1.5) + (4×4)×2=0.......(ii)

A B Aor R = 9.25 kN, R =18-R = 8.75 kN

if 0 x 2.5 m≤ ≤

( )x Bx M =R ×x - 4x. -2(x-2.5)2

2 2=8.75x - 2x - 2x + 5 = 6.75x - 2x + 5 ...(ii)

From (i) & (ii) we find out that bending movment at x = 2.1875 m in(i)gives maximum bending movement

2

max

dM[Just find for both the casses]dx

M 8.25 2.1875 2 1875 9.57 7K kNm= × − × =

Area movement of Inertia (I) = 3 3

5 40.1 0.2 6.6667 1012 12bh m−×

= = ×

Maximum distance from NA is y = 10 cm = 0.1m

3

2max 5

(9.57 10 ) 0.1 14.3556.6667 10

σ −

× ×= = =

×My N MPamI

Therefore maximum tensile stress in the lowest point in the beam is 14.355 MPa and maximum compressive stress in the topmost fiber of the beam is -14.355 MPa.

Conventional Question IES-2007 Question: A simply supported beam made of rolled steel joist (I-section: 450mm × 200mm) has

a span of 5 m and it carriers a central concentrated load W. The flanges are strengthened by two 300mm × 20mm plates, one riveted to each flange over the entire length of the flanges. The second moment of area of the joist about the principal bending axis is 35060 cm4. Calculate

(i) The greatest central load the beam will carry if the bending stress in the 300mm/20mm plates is not to exceed 125 MPa.

AB

RA R

B

X

1.5

4m

2KN4kN/M

X

C/s

B=10cm

NA


Chapter-6 Bending Stress in Beam S K Mondal’s (ii) The minimum length of the 300 mm plates required to restrict the maximum

bending stress is the flanges of the joist to 125 MPa. Answer:

Moment of Inertia of the total section about X-X

(I) = moment of inertia of I –section + moment of inertia of the plates about X-X axis.

2330 2 45 235060 2 30 2

12 2 2

⎡ ⎤⎛ ⎞×⎢ ⎥⎟⎜= + + × × + ⎟⎜⎢ ⎥⎟⎜⎝ ⎠⎢ ⎥⎣ ⎦ 4101370 cm=

( ) ( )σ6 8

(i) Greatest central point load(W):For a simply supported beam a concentrated load at centre.

WL 5M = 1.254 4

125 10 101370 10. 5171940.245

1.25W = 517194 or W = 413.76 kN

W W

IM Nmy

−

×= =

× × ×= = =

∴

(ii) Suppose the cover plates are absent for a distance of x-meters from each support. Then at these points the bending moment must not exceed moment of resistance of ‘I’ section alone i.e

( ) ( )σ8

635060 10. 125 10 178878

0.245I Nm

y

−×= × × =

moment at x metres from each support Bending∴



W= 178878241760, 178878

2 0.86464

leaving 0.86464 m from each support, for themiddle 5 - 2×0.86464 = 3.27 m the cover plate should beprovided.

x

or x

or x mHence

× =

× =

=

Conventional Question IES-2002 Question: A beam of rectangular cross-section 50 mm wide and 100 mm deep is simply

supported over a span of 1500 mm. It carries a concentrated load of 50 kN, 500 mm from the left support.

Calculate: (i) The maximum tensile stress in the beam and indicate where it occurs: (ii) The vertical deflection of the beam at a point 500 mm from the right support.

E for the material of the beam = 2 × 105 MPa. Answer: Taking moment about L

RR 1500 50 500, 16.667, 50

50 16.667=33.333 kN

R

L R

L

or R kNor R R

R

× = ×

=

+ =

∴ = −

Take a section from right R, x-x at a distance x.

xBending moment (M ) .RR x=+

Therefore maximum bending moment will occur at 'c' Mmax=16.667×1 KNm

(i) Moment of Inertia of beam cross-section

33

4 6 40.050 (0.100)( ) = 4.1667×1012 12

−×= =

bhI m m

( )3

2max 6

Applying bending equation0.00116.67 10

M σ 2or, σ / 200MPaI 4.1667 10

E My N my Iρ −

⎛ ⎞⎟⎜× × ⎟⎜ ⎟⎜⎝ ⎠= = = = =

×

It will occure where M is maximum at point 'C'

2

x 2

(ii) Macaulay's method for determing the deflectionof the beam will be convenient as there is point load.

M 33.333 50 ( 0.5)= = × − × −d yEI x xdx



2 22

1 22

2

3 31

1

Integrate both side we getd 50 EI 33.333 ( 0.5)

2 2 x=0, y=0 gives c 0 x=1.5, y=0 gives

0=5.556×(1.5) 8.333 1 1.5, 6.945

= × − − + +

=

− × + ×

=−

y x x c x cdx

atat

cor c

3 3

5 6 6

5.556 8.333( 0.5) 6.945 1 2.43

2.43, m = -2.9167 mm[downward so -ive](2×10 10 ) (4.1667 10 )

EIy x x

or y −

∴ = × − − − × =−

−=

× × ×

Conventional Question AMIE-1997 Question: If the beam cross-section is rectangular having a width of 75 mm, determine the

required depth such that maximum bending stress induced in the beam does not exceed 40 MN/m2

Answer: Given: b =75 mm =0·075 m, maxσ =40 MN/m2

Depth of the beam, d: Figure below shows a rectangular section of width b = 0·075 m and depth d metres. The bending is considered to take place about the horizontal neutral axis N.A. shown in the figure. The maximum bending stress occurs at the outer fibres of the rectangular

section at a distance d2

above or below the neutral axis. Any fibre at a distance y from N.A. is

subjected to a bending stress, MyI

σ = , where I denotes the second moment of area of the

rectangular section about the N.A. i.e.3bd

12.

At the outer fibres, y = d2

, the maximum bending stress there becomes

( )max 3 2

2

max

dMM2 i

bd bd12 6bdor M . (ii)6

σ

σ

⎛ ⎞× ⎜ ⎟⎝ ⎠= = − − − −

= − − − −

For the condition of maximum strength i.e. maximum moment M, the product bd2 must be a maximum, since maxσ is constant for a given material. To maximize the quantity bd2 we realise that it must be expressed in terms of one independent variable, say, b, and we may do this from the right angle triangle relationship.



2 2 2

2 2 2

b d Dor d D b

+ == −

Multiplying both sides by b, we get 2 2 3bd bD b= − To maximize bd2 we take the first derivative of expression with respect to b and set it equal to

zero, as follows:

( ) ( )= − = − = + − = − =2 2 3 2 2 2 2 2 2 2d dbd bD b D 3b b d 3b d 2b 0db db

Solving, we have, depth d 2 b ...(iii) This is the desired radio in order that the beam will carry a maximum moment M. It is to be noted that the expression appearing in the denominator of the right side of eqn. (i) i.

e. 2bd

6is the section modulus (Z) of a rectangular bar. Thus, it follows; the section modulus is

actually the quantity to be maximized for greatest strength of the beam. Using the relation (iii), we have d = 2 x 0·075 = 0·0106 m

Now, M = maxσ x Z = maxσ x2bd

6

Substituting the values, we get

M = 40 × ( )20.075 0.1066

× = 0.005618 MNm

( )( )

2max

M 0.005618 40MN / mZ 0.075 0.106 2 / 6

σ = = =×

Hence, the required depth d = 0·106 m = 106 mm Conventional Question IES-2009 Q. (i)A cantilever of circular solid cross-section is fixed at one end and carries a

concentrated load P at the free end. The diameter at the free end is 200 mm and increases uniformly to 400 mm at the fixed end over a length of 2 m. At what distance from the free end will the bending stresses in the cantilever be maximum? Also calculate the value of the maximum bending stress if the concentrated load P = 30 kN [15-Marks]

Ans. We have

Taking distance x from the free end we have

Let d be the diameter at x from free end.

From equation (i), we have

M .... (i)y Iσ =

( )

3

4

M = 30x kN.m = 30x × 10 N.mxy = 100 + 200 1002

100 50x mmdand I = 64

−

= +

π

( )

( )

4

44

400 200200 x

264

200 100x mm

64

⎡ ⎤−π +⎢ ⎥⎣ ⎦=

π +=



Hence maximum bending stress occurs at the midway and from equation (ii), maximum bending

stress

( )

( )

( )

3

3

4 12

3 12

100 50x 10

30x 10

200 100x 1064

960x 200 100x 10 ...... (ii)

−

−

−

σ+ ×

×=

π + ×

∴ σ = + ×π

( ) 3 12960x 200 100x 10

dFor max , 0dx

−= + ×π

σσ =

1210 960 ×∴

π

( )( ) ( ) ( )4 3x 3 100 200 100x 1. 200 100x 0− −⎡ ⎤− + + + =⎢ ⎥⎣ ⎦ - 300x + 200 + 100x = 0 x = 1m

⇒

⇒30kN

2000mm(2m)

200

400

( ) ( )

( )

3 12

12

3

960 1 200 100 10

960 10 11.32 MPa300

−σ = + ×π×= =

π ×


7. Shear Stress in Beam

Theory at a Glance (for IES, GATE, PSU) 1. Shear stress in bending (τ )

τ = vQIb

Where, V = Shear force = dMdx

Q = Statical moment = 1

1

c

y

ydA∫

I = Moment of inertia b = Width of beam c/s.

2. Statical Moment (Q)

Q=1

1

c

y

ydA∫ = Shaded Area × distance of the centroid of the shaded area from the neutral axis of the c/s.

3. Variation of shear stress Section Diagram Position of

maxτ maxτ

Rectangular

N.A

maxτ = 32VA

max 1.5τ τ= mean

NAτ=

Circular

N.A

max43

τ τ= mean

Triangular

6h

from N.A maxτ 1.5τ= mean

NAτ = 1.33τmean


Chapter-7 Shear Stress in Beam S K Mondal’s Trapezoidal

6h

from N.A

Section Diagram maxτ

Uni form

I-Section

In Flange,

( maxτ ) ( ) 2

11

2 1max

2 8h

hy

V hI

τ −=

⎡ ⎤= ⎣ ⎦

( )1 2

max hyoτ

==

In Web

( )1

2 2 2max 1 1 1( )

8y o

v b h h thIt

τ −=

⎡ ⎤= +⎣ ⎦

( )1

221m 1

2 8him y

vb h hIt

τ=

⎡ ⎤= −⎣ ⎦

4. Variation of shear stress for some more section [Asked in different examinations] Non uniform I-Section

Diagonally placed square section

L-section

Hollow circle

T-section

Cross

5. Rectangular section


Chapter-7 Shear Stress in Beam S K Mondal’s

• Maximum shear stress for rectangular beam: maxτ = 32VA

• For this, A is the area of the entire cross section

• Maximum shear occurs at the neutral axis

• Shear is zero at the top and bottom of beam

6. Shear stress in beams of thin walled profile section. • Shear stress at any point in the wall distance "s" from the free edge

force = Thickness of the section I = Moment of inrertia about NA

sx

o

x

V ydAIt

where V Shear

τ

τ

=

=

∫

• Shear Flow (q)

q =

sx

NA o

Vt ydAI

τ = ∫

• Shear Force (F)

F= ∫ qds

• Shear Centre (e) Point of application of shear stress resultant

B

Shearing occurs here

A

Vx

O





Shear Stress Variation GATE-1. The transverse shear stress acting

in a beam of rectangular cross-section, subjected to a transverse shear load, is:

(a) Variable with maximum at the bottom of the beam

(b) Variable with maximum at the top of the beam

(c) Uniform (d) Variable with maximum on the

neutral axis

[IES-1995, GATE-2008]

GATE-2. The ratio of average shear stress to the maximum shear stress in a beam with a square cross-section is: [GATE-1994, 1998]

2 3(a) 1 (b) (c) (d) 23 2

GATE-3. If a beam of rectangular cross-section is subjected to a vertical shear force V, the

shear force carried by the upper one third of the cross-section is [CE: GATE-2006]

(a) zero (b) 7V27

(c) 8V27

(d) V3

GATE-4. I-section of a beam is formed by gluing wooden planks as shown in the figure below.

If this beam transmits a constant vertical shear force of 3000 N, the glue at any of the four joints will be subjected to a shear force (in kN per meter length) of

50 mm 75 mm 200 mm

50 mm

200 mm

50 mm

[CE: GATE-2006] (a) 3.0 (b) 4.0 (c) 8.0 (d) 10.7 GATE-5. The shear stress at the neutral axis in a beam of triangular section with a base of 40

mm and height 20 mm, subjected to a shear force of 3 kN is [CE: GATE-2007] (a) 3 MPa (b) 6 MPa (c) 10 MPa (d) 20 MPa GATE-6. The point within the cross sectional plane of a beam through which the resultant of

the external loading on the beam has to pass through to ensure pure bending without twisting of the cross-section of the beam is called [CE: GATE-2009]


Chapter-7 Shear Stress in Beam S K Mondal’s (a) moment centre (b) centroid (c) shear centre (d) elastic centre


Shear Stress Variation IES-1. At a section of a beam, shear force is F with zero BM. The cross-section is square with

side a. Point A lies on neutral axis and point B is mid way between neutral axis and top edge, i.e. at distance a/4 above the neutral axis. If τ A and τ B denote shear stresses at points A and B, then what is the value of τ A / τ B? [IES-2005]

(a) 0 (b) ¾ (c) 4/3 (d) None of above IES-2. A wooden beam of rectangular cross-section 10 cm deep by 5 cm wide carries

maximum shear force of 2000 kg. Shear stress at neutral axis of the beam section is: [IES-1997]

(a) Zero (b) 40 kgf/cm2 (c) 60 kgf/cm2 (d) 80 kgf/cm2 IES-3. In case of a beam of circular cross-section subjected to transverse loading, the

maximum shear stress developed in the beam is greater than the average shear stress by: [IES-2006; 2008]

(a) 50% (b) 33% (c) 25% (d) 10% IES-4. What is the nature of distribution of shear stress in a rectangular beam?

[IES-1993, 2004; 2008] (a) Linear (b) Parabolic (c) Hyperbolic (d) Elliptic IES-5. Which one of the following statements is correct? [IES 2007] When a rectangular section beam is loaded transversely along the length, shear stress

develops on (a) Top fibre of rectangular beam (b) Middle fibre of rectangular beam (c) Bottom fibre of rectangular beam (d) Every horizontal plane IES-6. A beam having rectangular cross-section is subjected to an external loading. The

average shear stress developed due to the external loading at a particular cross-section is avgt . What is the maximum shear stress developed at the same cross-section

due to the same loading? [IES-2009]

(a) 12 avgt (b) avgt (c)

32 avgt (d) 2 avgt

IES-7. The transverse shear stress

acting in a beam of rectangular cross-section, subjected to a transverse shear load, is:

(a) Variable with maximum at the bottom of the beam

(b) Variable with maximum at the top of the beam

(c) Uniform (d) Variable with maximum on the

neutral axis


Chapter-7 Shear Stress in Beam S K Mondal’s [IES-1995, GATE-2008]

IES-8.

A cantilever is loaded by a concentrated load P at the free end as shown. The shear stress in the element LMNOPQRS is under consideration. Which of the following figures represents the shear stress directions in the cantilever?

[IES-2002]

IES-9. In I-Section of a beam subjected to transverse shear force, the maximum shear stress

is developed. [IES- 2008] (a) At the centre of the web (b) At the top edge of the top flange (c) At the bottom edge of the top flange (d) None of the above IES-10. The given figure (all

dimensions are in mm) shows an I-Section of the beam. The shear stress at point P (very close to the bottom of the flange) is 12 MPa. The stress at point Q in the web (very close to the flange) is:

(a) Indeterminable due to incomplete data

(b) 60MPa (c) 18 MPa (d) 12 MPa

[IES-2001]IES-11. Assertion (A): In an I-Section beam subjected to concentrated loads, the shearing

force at any section of the beam is resisted mainly by the web portion. Reason (R): Average value of the shearing stress in the web is equal to the value of

shearing stress in the flange. [IES-1995] (a) Both A and R are individually true and R is the correct explanation of A (b) Both A and R are individually true but R is NOT the correct explanation of A (c) A is true but R is false (d) A is false but R is true


Chapter-7 Shear Stress in Beam S K Mondal’s IES-11(i). Statement (I): If the bending moment along the length of a beam is constant, then the beam

cross-section will not experience any shear stress. [IES-2012] Statement (II): The shear force acting on the beam will be zero everywhere along its length. (a) Both Statement (I) and Statement (II) are individually true and Statement (II) is the correct explanation of Statement (I) (b) Both Statement (I) and Statement (II) are individually true but Statement (II) is not the correct explanation of Statement (I) (c) Statement (I) is true but Statement (II) is false (d) Statement (I) is false but Statement (II) is true

Shear stress distribution for different section IES-12. The shear stress distribution over a beam cross-

section is shown in the figure above. The beam is of (a) Equal flange I-Section (b) Unequal flange I-Section (c) Circular cross-section (d) T-section

[IES-2003]


Shear Stress Variation IAS-1. Consider the following statements: [IAS-2007] Two beams of identical cross-section but of different materials carry same bending

moment at a particular section, then 1. The maximum bending stress at that section in the two beams will be same. 2. The maximum shearing stress at that section in the two beams will be same. 3. Maximum bending stress at that section will depend upon the elastic modulus of

the beam material. 4. Curvature of the beam having greater value of E will be larger. Which of the statements given above are correct? (a) 1 and 2 only (b) 1, 3 and 4 (c) 1, 2 and 3 (d) 2, 3 and 4 IAS-2. In a loaded beam under bending [IAS-2003] (a) Both the maximum normal and the maximum shear stresses occur at the skin fibres (b) Both the maximum normal and the maximum shear stresses occur the neutral axis (c) The maximum normal stress occurs at the skin fibres while the maximum shear stress

occurs at the neutral axis (d) The maximum normal stress occurs at the neutral axis while the maximum shear stress

occurs at the skin fibres

Shear stress distribution for different section IAS-3. Select the correct shear stress distribution diagram for a square beam with a

diagonal in a vertical position: [IAS-2002]



IAS-4. The distribution of shear stress of a beam is shown in the given figure. The cross-

section of the beam is: [IAS-2000]

IAS-5. A channel-section of the beam shown in the given figure carries a uniformly

distributed load. [IAS-2000]

Assertion (A): The line of action of the load passes through the centroid of the cross-

section. The beam twists besides bending. Reason (R): Twisting occurs since the line of action of the load does not pass through

the web of the beam. (a) Both A and R are individually true and R is the correct explanation of A (b) Both A and R are individually true but R is NOT the correct explanation of A (c) A is true but R is false (d) A is false but R is true



OBJECTIVE ANSWERS

GATE-1. Ans (d)

GATE-2. Ans. (b)

GATE-3. Ans. (b)

Integrating both sides, we get

GATE-4. Ans. (b)

Shear flow,

meanττ23

max =

max mean32

τ τ=

d2

y

τ = SAI

yb

⎛ ⎞⎛ ⎞ +⎜ ⎟⎜ ⎟⎛ ⎞ ⎝ ⎠⎜ ⎟× − × ×⎜ ⎟⎝ ⎠ ⎝ ⎠=

2V2 2

I

d yd y b

b

⇒

⎛ ⎞× −⎜ ⎟⎝ ⎠τ =

22V

42I

d y

∴ = τ ×Fd b dy

⎛ ⎞× −⎜ ⎟⎝ ⎠= ×

22V

42I

d yb dy

⇒⎛ ⎞

= −⎜ ⎟⎝ ⎠∫

222

6

VF2I 4

d

d

b d y dy

⎡ ⎤ ⎡ ⎤= − = − − +⎢ ⎥ ⎢ ⎥⎣ ⎦ ⎣ ⎦

2 3 3 3 3 32

6

V V2I 4 3 2I 8 24 24 648

d

d

b d y b d d d dy

= × × = × × × =3 3

3V 28 V 28 7 V122I 8 81 8 81 272

b d b dbd

= VQI

q

⎡ ⎤× ×= + × + × ×⎢ ⎥⎣ ⎦

3 3250 300 150 50I 2 150 50 125

12 12


Chapter-7 Shear Stress in Beam S K Mondal’s For any of the four joints, Q = 50 × 75 × 125 =

Note: In the original Question Paper, the figure of the beam was draw as I-section but in language of the question, it was mentioned as T-section. Therefore, there seems to be an error in the question.

GATE-5. Ans. (c)

Shear stress,

Where S = Shear force A = Area above the level where shear stress is desired = Distance of CG of area A from neutral axis I = Moment of Inertia about neutral axis b = Width of the section at the level where shear stress is desired.

Width at a distance of mm from the top =

Alternatively,

GATE-6. Ans. (c)

IES ANSWERS

IES-1. Ans. (c)

= × 8 43.5 10 mm

3468750 mm

∴ ×= = =× 8

3000 468750 4.0 N/ mm 4.0 kN/ m3.5 10

q

τ = SAI

yb

y

40 mm

403 mm

20 mm

403

× =40 40 80 mm20 3 3

∴

⎛ ⎞ ⎛ ⎞× × × × × ×⎜ ⎟ ⎜ ⎟⎝ ⎠ ⎝ ⎠τ =⎛ ⎞× ×⎜ ⎟⎝ ⎠

3

3

1 80 40 1 403 102 3 3 3 340 20 80

36 3× × × × ×= =

× ×

3

33 10 3200 40 36 3 10 MPa

162 3200 20

= − 23

12S ( )q hy ybh

⎡ ⎤× × ⎛ ⎞= × − =⎢ ⎥⎜ ⎟⎝ ⎠× ⎣ ⎦

23

312 3 10 20 2020 10MPa

3 340 20

( )

22 2

32 2 A

4 3 2B 2

3

a a 3 VV y .a2 4VAy 3 V 42 aa 4y orIb 2 3a a 3 V aa . . a 412 2 4a

τττ

⎛ ⎞× −⎜ ⎟

⎝ ⎠= = = − = =⎧ ⎫⎛ ⎞⎪ ⎪⎛ ⎞× −⎜ ⎟⎨ ⎬⎜ ⎟⎜ ⎟⎝ ⎠⎪ ⎪⎝ ⎠⎩ ⎭



IES-2. Ans. (c) Shear stress at neutral axis =

IES-3. Ans. (b) In the case of beams with circular cross-section, the ratio of the maximum shear stress to average shear stress 4:3

IES-4. Ans. (b)

indicating a parabolic distribution of shear stress across the cross-section.

IES-5. Ans. (b)

IES-6. Ans. (c)

Shear stress in a rectangular

beam, maximum shear stress,

Shear stress in a circular beam, the maximum shear stress,

IES-7. Ans (d)

IES-8. Ans. (d) IES-9. Ans. (a) IES-10. Ans. (b) IES-11. Ans. (c) IES-11(i). Ans. (a) IES-12. Ans. (b)

23 3 2000 60kg/cm2 2 10 5

Fbd

× = × =×

221

V h y4I 4

τ ⎛ ⎞= −⎜ ⎟

⎝ ⎠

τ = = τmax (average)3F 1.5

2b. hτ = = τ

π×max (average)

2

4F 433 d

4

meanττ23

max =



IAS-1. Ans. (a) Bending stress = and shear stress ( ) = both of them does not depends on

material of beam. IAS-2. Ans. (c)

indicating a parabolic distribution of shear stress across the cross-section.

IAS-3. Ans. (d) IAS-4. Ans. (b) IAS-5. Ans. (c) Twisting occurs since the line of action of the load does not pass through the shear.


Conventional Question IES-2006 Question: A timber beam 15 cm wide and 20 cm deep carries uniformly distributed load over a

span of 4 m and is simply supported. If the permissible stresses are 30 N/mm2 longitudinally and 3 N/mm2 transverse

shear, calculate the maximum load which can be carried by the timber beam.

Answer: ( ) ( )33

4 40.15 0.20Moment of inertia (I) 10 m

12 12bh −×

= = =

δ MyI

τ VAyIb

221

V h y4I 4

τ⎛ ⎞

= −⎜ ⎟⎝ ⎠

Nm

ω

20cmN/A



2 2

20Distance of neutral axis from the top surface 10cm 0.1 m2

We know that or

Where maximum bending moment due to uniformly4distributed load in simply supported beam ( ) 2

8 8Cons

y

M MyI y I

M

σ σ

ω ω ω

= = =

= =

×= = =

( )64

idering longitudinal stress2 0.1

30 1010

or, 15 kN/m

ω

ω

−

×× =

=

mean

max

6

Now consideng Shear . .4Maximum shear force 22 2

2Therefore average shear stress ( ) 66.670.15 0.2

For rectangular cross-section3 3Maximum shear stress( ) . 66.67 1002 2

Now 3 10 100 ;

Lω ω ω

ωτ ω

τ τ ω ω

ω ω

= = =

= =×

= = × =

× = 30 kN/mSo maximum load carring capacity of the beam = 15 kN/m (without fail).

=


8. Fixed and Continuous Beam

Theory at a Glance (for IES, GATE, PSU) What is a beam? A (usually) horizontal structural member that is subjected to a load that tends to bend it.

Types of Beams

Simply supported beam

Cantilever beam

Simply Supported Beams

Cantilever Beam

Continuous Beam

Single Overhang Beam

Double Overhang Beam

Single Overhang Beam with internal hinge

Fixed Beam

Continuous beam

Continuous beams Beams placed on more than 2 supports are called continuous beams. Continuous beams are used when

the span of the beam is very large, deflection under each rigid support will be equal zero.

Analysis of Continuous Beams (Using 3-moment equation)

Stability of structure

If the equilibrium and geometry of structure is maintained under the action of forces than the structure

is said to be stable.


Chapter-8 Fixed and Continuous Beam Page-286

External stability of the structure is provided by the reaction at the supports. Internal stability is

provided by proper design and geometry of the member of the structure.

Statically determinate and indeterminate structures

Beams for which reaction forces and internal forces can be found out from static equilibrium equations

alone are called statically determinate beam.

Example:

i A .0, 0 and M 0 is sufficient to calculate R &i i BX Y R= = =∑ ∑ ∑

Beams for which reaction forces and internal forces cannot be found out from static equilibrium

equations alone are called statically indeterminate beam. This type of beam requires deformation

equation in addition to static equilibrium equations to solve for unknown forces.

Example:

RA RB RcRD

P P

RA

RB

P



Advantages of fixed ends or fixed supports • Slope at the ends is zero.

• Fixed beams are stiffer, stronger and more stable than SSB.

• In case of fixed beams, fixed end moments will reduce the BM in each section.

• The maximum deflection is reduced.

Bending moment diagram for fixed beam Example:

BMD for Continuous beams BMD for continuous beams can be obtained by superimposing the fixed end moments diagram over the

free bending moment diagram.



Three - moment Equation for continuous beams OR Clapeyron’s Three Moment Equation





Overhanging Beam IES-1. An overhanging beam ABC is supported at points A and B, as shown in the above

figure. Find the maximum bending moment and the point where it occurs. [IES-2009]

(a) 6 kN-m at the right support (b) 6 kN-m at the left support (c) 4.5 kN-m at the right support (d) 4.5 kN-m at the midpoint

between the supports

IES-2. A beam of length 4 L is simply supported on two supports with equal overhangs of L on either sides and carries three equal loads, one each at free ends and the third at the mid-span. Which one of the following diagrams represents correct distribution of shearing force on the beam? [IES-2004]

IES-3. A horizontal beam carrying uniformly distributed load is supported with equal overhangs as shown in the given figure

The resultant bending moment at the mid-span shall be zero if a/b is: [IES-2001] (a) 3/4 (b) 2/3 (c) 1/2 (d) 1/3




Overhanging Beam IAS-1.

If the beam shown in the given figure is to have zero bending moment at its

middle point, the overhang x should be: [IAS-2000] (a) 2 / 4wl P (b) 2 / 6wl P (c) 2 / 8wl P (d) 2 /12wl P

IAS-2. A beam carrying a uniformly distributed load rests on two supports 'b' apart with equal overhangs 'a' at each end. The ratio b/a for zero bending moment at mid-span is: [IAS-1997]

(a) 12

(b) 1 (c) 32

(d) 2

IAS-3. A beam carries a uniformly distributed load and is supported with two equal overhangs as shown in figure 'A'. Which one of the following correctly shows the bending moment diagram of the beam? [IAS 1994]



OBJECTIVE ANSWERS

IES-1. Ans. (a) Taking moment about A

∴ Maximum Bending Moment = 6 kN-m at the right support

IES-2. Ans. (d)

They use opposite sign conversions but for correct sign remember S.F & B.M of cantilever is

(-) ive. IES-3. Ans. (c)

IAS-1. Ans. (c)

Bending moment at mid point (M) =

IAS-2. Ans. (d)

(i) By similarity in the B.M diagram a must be b/2

(ii) By formula gives a = b/2

IAS-3. Ans. (a)

( ) ( )B

B

B

A B

A

V 2 = 2 1 6 32V 2 18

V 10 kNV V 2 6 8kN

V 8 10 2 kN

× × + ×

⇒ = +⇒ =

+ = + =∴ = − = −

2c DwlR R P= = +

2

02 4 2 2 8Dwl l l l wlR P x gives x

P⎛ ⎞− × + × − + = =⎜ ⎟⎝ ⎠

22bM a 0

2 4ω ⎡ ⎤

= − =⎢ ⎥⎣ ⎦




Conventional Question IES-2006 Question: What are statically determinate and in determinate beams? Illustrate each case

through examples. Answer: Beams for which reaction forces and internal forces can be found out from static

equilibrium equations alone are called statically determinate beam. Example:

i

A .

0, 0 and M 0 is sufficient

to calculate R &i i

B

X Y

R

= = =∑ ∑ ∑

Beams for which reaction forces and internal forces cannot be found out from static equilibrium equations alone are called statically indeterminate beam. This type of beam requires deformation equation in addition to static equilibrium equations to solve for unknown forces.

Example:

RA RB RcRD

P P

RA

RB

P


9. Torsion

Theory at a Glance (for IES, GATE, PSU) • In machinery, the general term “shaft” refers to a member, usually of circular cross-

section, which supports gears, sprockets, wheels, rotors, etc., and which is subjected to

torsion and to transverse or axial loads acting singly or in combination.

• An “axle” is a rotating/non-rotating member that supports wheels, pulleys,… and

carries no torque.

• A “spindle” is a short shaft. Terms such as lineshaft, headshaft, stub shaft, transmission

shaft, countershaft, and flexible shaft are names associated with special usage.

Torsion of circular shafts

1. Equation for shafts subjected to torsion "T"

T G= =J L

τ θR

Torsion Equation

Where J = Polar moment of inertia

τ = Shear stress induced due to torsion T.

G = Modulus of rigidity

θ = Angular deflection of shaft

R, L = Shaft radius & length respectively

Assumptions

• The bar is acted upon by a pure torque.

• The section under consideration is remote from the point of application of the load and from

a change in diameter.

• Adjacent cross sections originally plane and parallel remain plane and parallel after

twisting, and any radial line remains straight.

• The material obeys Hooke’s law

• Cross-sections rotate as if rigid, i.e. every diameter rotates through the same angle


Chapter-9 Torsion S K Mondal’s

2. Polar moment of inertia

• Solid shaft “J” = 4d

32π

• Hollow shaft, "J” = 4 4( )32π −o id d

3. The polar section modulus

Zp= J / c, where c = r = D/2

• For a solid circular cross-section, Zp = π D3 / 16

• For a hollow circular cross-section, Zp = π (Do4 - Di4 ) / (16Do)

• Then, maxτ = T / Zp

• If design shears stress, dτ is known, required polar section modulus can be calculated from:

Zp = T / dτ

4. Power Transmission (P)

• P (in Watt ) = 2

60NTπ

• P (in hp) = 24500

NTπ (1 hp = 75 Kgm/sec).

As stated above, the polar second moment of area, J is defined as J = 2 3

0π r dr

Rz

For a solid shaft J = 24

24 32

4

0

4 4

π π πr R DRL

NMOQP = = (6)

For a hollow shaft of internal radius r:

J = 2 3

0π r dr

Rz = 24 2 32

44 4 4 4π π πr R r D d

r

RLNMOQP = − = −( ) c h (7)

Where D is the external and d is the internal diameter.



[Where N = rpm; T = Torque in N-m.]

5. Safe diameter of Shaft (d) • Stiffness consideration

θ=T G

J L

• Shear Stress consideration

TJ R

τ=

We take higher value of diameter of both cases above for overall safety if other parameters are given.

6. In twisting

• Solid shaft, maxτ = 3

16Tdπ

• Hollow shaft, maxτ = o4 4

16Td( )π −o id d

• Diameter of a shaft to have a maximum deflection "α " d = 4.9 × 4

αTLG

[Where T in N-mm, L in mm, G in N/mm2]

7. Comparison of solid and hollow shaft • A Hollow shaft will transmit a greater torque than a solid shaft of the same weight & same

material because the average shear stress in the hollow shaft is smaller than the average

shear stress in the solid shaft

• max

max

( ) shaft 16( ) shaft 15ττ

=holloowsolid

o i

If solid shaft dia = DDHollow shaft, d = D, d = 2

⎡ ⎤⎢ ⎥⎢ ⎥⎣ ⎦

• Strength comparison (same weight, material, length and maxτ )

2

2

11

h

s

T nT n n

+=−

Externaldiameter of hollow shaftWhere, n=Internaldiameter of hollow shaft

[ONGC-2005]

• Weight comparison (same Torque, material, length and maxτ )

( )( )

2 2/3

2/34

1

1h

s

n nWW n

−=

− Externaldiameter of hollow shaftWhere, n=

Internaldiameter of hollow shaft [WBPSC-2003]

• Strain energy comparison (same weight, material, length and maxτ )

2

2

1h

s

U nU n

+= 2

11n

= +



8. Shaft in series

1 2θ θ θ= +

Torque (T) is same in all section

Electrical analogy gives torque(T) = Current (I)

9. Shaft in parallel

1 2θ θ= and 1 2T T T= +

Electrical analogy gives torque(T) = Current (I)

10. Combined Bending and Torsion • In most practical transmission situations shafts which carry torque are also subjected to

bending, if only by virtue of the self-weight of the gears they carry. Many other practical

applications occur where bending and torsion arise simultaneously so that this type of

loading represents one of the major sources of complex stress situations.

• In the case of shafts, bending gives rise to tensile stress on one surface and compressive

stress on the opposite surface while torsion gives rise to pure shear throughout the shaft.

• For shafts subjected to the simultaneous application of a bending moment M and torque T

the principal stresses set up in the shaft can be shown to be equal to those produced by an

equivalent bending moment, of a certain value Me acting alone.

• Figure

• Maximum direct stress ( xσ ) & Shear stress ( ( )xyτ in element A

3

3

32

16

σπ

τπ

= +

=

x

xy

M Pd ATd

• Principal normal stresses ( 1,2σ ) & Maximum shearing stress ( maxτ )

1,2σ = 2

2

2 2σ σ τ⎛ ⎞± +⎜ ⎟

⎝ ⎠x x

xy

2

21 2max ( )

2 2σσ στ τ− ⎛ ⎞= = ± +⎜ ⎟⎝ ⎠

xxy



• Maximum Principal Stress ( maxσ ) & Maximum shear stress ( maxτ )

maxσ = 2 23

16π

⎡ ⎤+ +⎣ ⎦M M Td

maxτ = 2 23

16π

+M Td

• Location of Principal plane (θ )

θ = 11 tan2

− ⎛ ⎞⎜ ⎟⎝ ⎠

TM

• Equivalent bending moment (Me) & Equivalent torsion (Te).

2 2

2

⎡ ⎤+ += ⎢ ⎥⎢ ⎥⎣ ⎦

eM M TM

2 2= +eT M T

• Important Note

o Uses of the formulas are limited to cases in which both M & T are known. Under any

other condition Mohr’s circle is used.

• Safe diameter of shaft (d) on the basis of an allowable working stress.

o wσ in tension , d = 332 e

w

Mπσ

o wτ in shear , d= 316 e

w

Tπτ

11. Shaft subjected to twisting moment only • Figure

• Normal force ( nF ) & Tangential for ( tF ) on inclined plane AB

[ ][ ]

sin + AC cos

× BC cos - AC sin

τ θ θτ θ θ

= − ×

=n

t

F BC

F



• Normal stress ( nσ ) & Tangential stress (shear stress) ( tσ ) on inclined plane AB.

nσ = sin 2τ θ−

tσ = 2τ θcos

• Maximum normal & shear stress on AB

θ ( nσ )max τ max

0 0 +τ

45° –τ 0

90 0 –τ

135 +τ 0

• Important Note

• Principal stresses at a point on the surface of the shaft = +τ , -τ , 0

i.e 1,2 sin2σ τ θ= ±

• Principal strains

1 2 3(1 ); (1 ); 0τ τμ μ∈ = + ∈ = − + ∈ =E E

• Volumetric strain,

1 2 3 0∈ =∈ +∈ +∈ =v

• No change in volume for a shaft subjected to pure torque.

12. Torsional Stresses in Non-Circular Cross-section Members • There are some applications in machinery for non-circular cross-section members and shafts

where a regular polygonal cross-section is useful in transmitting torque to a gear or pulley

that can have an axial change in position. Because no key or keyway is needed, the

possibility of a lost key is avoided.

• Saint Venant (1855) showed that maxτ in a rectangular b × c section bar occurs in the middle

of the longest side b and is of magnitude formula

max 2 21.83

/T T

b cbc bcτ

α⎛ ⎞= = +⎜ ⎟⎝ ⎠

Where b is the longer side and α factor that is function of the ratio b/c.

The angle of twist is given by

3Tlbc G

θβ

=

Where β is a function of the ratio b/c



Shear stress distribution in different cross-section

Rectangular c/s Elliptical c/s Triangular c/s

13. Torsion of thin walled tube • For a thin walled tube

Shear stress,02

τ = TA t

Angle of twist, 2 O

sLA Gτφ =

[Where S = length of mean centre line, OA = Area enclosed by mean centre line]

• Special Cases

o For circular c/s

3 22 ; ; 2π π π= = =oJ r t A r S r

[r = radius of mean Centre line and t = wall thickness]

2

. =2 r 2

τπ

∴ = =o

T T r Tt J A t

32τϕ

π= = =

o

TL L TLGJ A JG r tG

o For square c/s of length of each side ‘b’ and thickness ‘t’

2

0

=4b A bS

=

o For elliptical c/s ‘a’ and ‘b’ are the half axis lengths.

0

3 ( )2

A ab

S a b ab

π

π

=

⎡ ⎤≈ + −⎢ ⎥⎣ ⎦





Torsion Equation GATE-1. A solid circular shaft of 60 mm diameter transmits a torque of 1600 N.m. The

value of maximum shear stress developed is: [GATE-2004] (a) 37.72 MPa (b) 47.72 MPa (c) 57.72 MPa (d) 67.72 MPa GATE-2. Maximum shear stress developed on the surface of a solid circular shaft under

pure torsion is 240 MPa. If the shaft diameter is doubled then the maximum shear stress developed corresponding to the same torque will be: [GATE-2003]

(a) 120 MPa (b) 60 MPa (c) 30 MPa (d) 15 MPa GATE-2(i) A long shaft of diameter d is subjected to twisting moment T at its ends. The

maximum normal stress acting at its cross-section is equal to [CE: GATE-2006]

(a) zero (b) 316T

dπ (c) 3

32Tdπ

(d) 364 T

dπ

GATE-3. A steel shaft 'A' of diameter 'd' and length 'l' is subjected to a torque ‘T’ Another shaft 'B' made of aluminium of the same diameter 'd' and length 0.5l is also subjected to the same torque 'T'. The shear modulus of steel is 2.5 times the shear modulus of aluminium. The shear stress in the steel shaft is 100 MPa. The shear stress in the aluminium shaft, in MPa, is: [GATE-2000]

(a) 40 (b) 50 (c) 100 (d) 250 GATE-4. For a circular shaft of diameter d subjected to torque T, the maximum value of

the shear stress is: [GATE-2006]

3 3 3 3

64 32 16 8(a) (b) (c) (d)T T T Td d d dπ π π π

GATE-4a. A torque T is applied

at the free end of a stepped rod of circular cross-sections as shown in the figure. The shear modulus of the material of the rod is G. The expression for d to produce an angular twist θ at the free end is

d2d

L L/2

T

[GATE-2011]

(a) 1432 TL

Gπθ⎛ ⎞⎜ ⎟⎝ ⎠

(b) 1418 TL

Gπθ⎛ ⎞⎜ ⎟⎝ ⎠

(c) 1416 TL

Gπθ⎛ ⎞⎜ ⎟⎝ ⎠

(d) 142 TL

Gπθ⎛ ⎞⎜ ⎟⎝ ⎠

Power Transmitted by Shaft GATE-5. The diameter of shaft A is twice the diameter or shaft B and both are made of

the same material. Assuming both the shafts to rotate at the same speed, the maximum power transmitted by B is: [IES-2001; GATE-1994]

(a) The same as that of A (b) Half of A (c) 1/8th of A (d) 1/4th of A



GATE-5(i) A hollow circular shaft has an outer diameter of 100 mm and a wall thickness

of 25 mm. The allowable shear stress in the shaft is 125 MPa. The maximum torque the shaft can transmit is [CE: GATE-2009]

(a) 46 kN-m (b) 24.5 kN-m (c) 23 kN-m (d) 11.5 kN-m

Combined Bending and Torsion GATE-6. A solid shaft can resist a bending moment of 3.0 kNm and a twisting moment of

4.0 kNm together, then the maximum torque that can be applied is: [GATE-1996] (a) 7.0 kNm (b) 3.5 kNm (c)4.5 kNm (d) 5.0 kNm

Comparison of Solid and Hollow Shafts GATE-7. The outside diameter of a hollow shaft is twice its inside diameter. The ratio of

its torque carrying capacity to that of a solid shaft of the same material and the same outside diameter is: [GATE-1993; IES-2001]

(a) 1516

(b) 34

(c) 12

(d) 1

16

GATE-7(i) The maximum and minimum shear stresses in a hollow circular shaft of outer

diameter 20 mm and thickness 2 mm, subjected to a torque of 92.7 N-m will be (a) 59 MPa and 47.2 MPa (b) 100 MPa and 80 MPa [CE: GATE-2007] (c) 118 MPa and 160 MPa (d) 200 MPa and 160 Mpa GATE-7(ii)The maximum shear stress in a solid shaft of circular cross-section having

diameter d subjected to a torque T is .τ If the torque is increased by four times and the diameter of the shaft is increased by two times, the maximum shear stress in the shaft will be [CE: GATE-2008]

(a) 2τ (b) τ (c) 2τ (d)

4τ

Shafts in Series GATE-8. A torque of 10 Nm is transmitted through a stepped shaft as shown in figure.

The torsional stiffness of individual sections of lengths MN, NO and OP are 20 Nm/rad, 30 Nm/rad and 60 Nm/rad respectively. The angular deflection between the ends M and P of the shaft is: [GATE-2004]

(a) 0.5 rad (b) 1.0 rad (c) 5.0 rad (d) 10.0 rad

Shafts in Parallel GATE-9. The two shafts AB and BC, of equal

length and diameters d and 2d, are made of the same material. They are joined at B through a shaft coupling, while the ends A and C are built-in (cantilevered). A twisting moment T is applied to the coupling. If TA and TC represent the twisting moments at the ends A and C, respectively, then

[GATE-2005]



(a) TC = TA (b) TC =8 TA (c) TC =16 TA (d) TA=16 TC GATE-10. A circular shaft shown in the figure is subjected to torsion T at two points A

and B. The torsional rigidity of portions CA and BD is 1GJ and that of portion AB is 2GJ . The rotations of shaft at points A and B are 1 2and .θ θ The rotation

1θ is [CE: GATE-2005]

L

A B C D

L L L T T

(a) 1 2

TLGJ GJ+

(b) 1

TLGJ

(c) 2

TLGJ

(d) 1 2

TLGJ GJ−


Torsion Equation IES-1. Consider the following statements: [IES- 2008] Maximum shear stress induced in a power transmitting shaft is: 1. Directly proportional to torque being transmitted. 2. Inversely proportional to the cube of its diameter. 3. Directly proportional to its polar moment of inertia. Which of the statements given above are correct? (a) 1, 2 and 3 (b) 1 and 3 only (c) 2 and 3 only (d) 1 and 2 only IES-2. A solid shaft transmits a torque T. The allowable shearing stress is τ . What is

the diameter of the shaft? [IES-2008]

3 3 3 316T 32T 16T T(a) (b) (c) (d)πτ πτ τ τ

IES-2(i). If a solid circular shaft of steel 2 cm in diameter is subjected to a permissible

shear stress 10 kN/cm2, then the value of the twisting moment (Tr ) will be (a) 10π kN-cm (b) 20π kN-cm (c) 15π kN-cm (d) 5π kN-cm [IES-2012]

IES-3. Maximum shear stress developed on the surface of a solid circular shaft under

pure torsion is 240 MPa. If the shaft diameter is doubled, then what is the maximum shear stress developed corresponding to the same torque? [IES-2009]

(a) 120 MPa (b) 60 MPa (c) 30 MPa (d) 15 MPa IES-4. The diameter of a shaft is increased from 30 mm to 60 mm, all other conditions

remaining unchanged. How many times is its torque carrying capacity increased? [IES-1995; 2004]

(a) 2 times (b) 4 times (c) 8 times (d) 16 times IES-5. A circular shaft subjected to twisting moment results in maximum shear stress

of 60 MPa. Then the maximum compressive stress in the material is: [IES-2003] (a) 30 MPa (b) 60 MPa (c) 90 MPa (d) 120 MPa



IES-5(i). The boring bar of a boring machine is 25 mm in diameter. During operation, the bar gets twisted though 0.01 radians and is subjected to a shear stress of 42 N/mm2. The length of the bar is (Taking G = 0.84 × 105 N/mm2) [IES-2012]

(a) 500 mm (b) 250 mm (c) 625 mm (d) 375 mm IES-5(ii). The magnitude of stress induced in a shaft due to applied torque varies

(a) From maximum at the centre to zero at the circumference (b) From zero at the centre to maximum at the circumference [IES-2012] (c) From maximum at the centre to minimum but not zero at the circumference (d) From minimum but not zero at the centre, to maximum at the circumference

IES-6. Angle of twist of a shaft of diameter ‘d’ is inversely proportional to [IES-2000] (a) d (b) d2 (c) d3 (d) d4 IES-6a A solid steel shaft of diameter d and length l is subjected to twisting

moment T. Another shaft B of brass having same diameter d, but length l/2 is also subjected to the same moment. If shear modulus of steel is two times that of brass, the ratio of the angular twist of steel to that of brass shaft is: (a) 1:2 (b) 1:1 (c) 2:1 (d) 4:1 [IES-2011]

IES-7. A solid circular shaft is subjected to pure torsion. The ratio of maximum shear

to maximum normal stress at any point would be: [IES-1999] (a) 1 : 1 (b) 1: 2 (c) 2: 1 (d) 2: 3 IES-8. Assertion (A): In a composite shaft having two concentric shafts of different

materials, the torque shared by each shaft is directly proportional to its polar moment of inertia. [IES-1999]

Reason (R): In a composite shaft having concentric shafts of different materials, the angle of twist for each shaft depends upon its polar moment of inertia.

(a) Both A and R are individually true and R is the correct explanation of A (b) Both A and R are individually true but R is NOT the correct explanation of A (c) A is true but R is false (d) A is false but R is true IES-9. A shaft is subjected to torsion as shown. [IES-2002]

Which of the following figures represents the shear stress on the element

LMNOPQRS ?



IES-10. A round shaft of diameter 'd' and length 'l' fixed at both ends 'A' and 'B' is subjected to a twisting moment 'T’ at 'C', at a distance of 1/4 from A (see figure). The torsional stresses in the parts AC and CB will be:

(a) Equal (b) In the ratio 1:3 (c) In the ratio 3 :1 (d) Indeterminate

[IES-1997] IES-10(i). A power transmission solid shaft of diameter d length l and rigidity modulus G

is subjected to a pure torque. The maximum allowable shear stress is max .τ The maximum strain energy/unit volume in the shaft is given by: [IES-2013]

(a) 2max

4Gτ (b)

2max

2Gτ (c)

2max2

3Gτ (d)

2max

3Gτ

Hollow Circular Shafts IES-11. One-half length of 50 mm diameter steel rod is solid while the remaining half is

hollow having a bore of 25 mm. The rod is subjected to equal and opposite torque at its ends. If the maximum shear stress in solid portion is τ or, the maximum shear stress in the hollow portion is: [IES-2003]

(a) 1516

τ (b) τ (c) 43τ (d)

1615τ

Power Transmitted by Shaft IES-12. In power transmission shafts, if the polar moment of inertia of a shaft is

doubled, then what is the torque required to produce the same angle of twist? [IES-2006]

(a) 1/4 of the original value (b) 1/2 of the original value (c) Same as the original value (d) Double the original value IES-13. While transmitting the same power by a shaft, if its speed is doubled, what

should be its new diameter if the maximum shear stress induced in the shaft remains same? [IES-2006]

(a) 12

of the original diameter (b) 12

of the original diameter

(c) 2 of the original diameter (d) ( ) 1

3

1

2of the original diameter

IES-14. For a power transmission shaft transmitting power P at N rpm, its diameter is proportional to: [IES-2005]

(a)1/3P

N⎛ ⎞⎜ ⎟⎝ ⎠

(b) 1/2P

N⎛ ⎞⎜ ⎟⎝ ⎠

(c) 2/3P

N⎛ ⎞⎜ ⎟⎝ ⎠

(d) PN

⎛ ⎞⎜ ⎟⎝ ⎠



IES-15. A shaft can safely transmit 90 kW while rotating at a given speed. If this shaft is replaced by a shaft of diameter double of the previous one and rotated at half the speed of the previous, the power that can be transmitted by the new shaft is: [IES-2002]

(a) 90 kW (b) 180 kW (c) 360 kW (d) 720 kW IES-16. The diameter of shaft A is twice the diameter or shaft B and both are made of

the same material. Assuming both the shafts to rotate at the same speed, the maximum power transmitted by B is: [IES-2001; GATE-1994]

(a) The same as that of A (b) Half of A (c) 1/8th of A (d) 1/4th of A IES-17. When a shaft transmits power through gears, the shaft experiences [IES-1997] (a) Torsional stresses alone (b) Bending stresses alone (c) Constant bending and varying torsional stresses (d) Varying bending and constant torsional stresses

Combined Bending and Torsion IES-18. The equivalent bending moment under combined action of bending moment M

and torque T is: [IES-1996; 2008; IAS-1996]

(a) 2 2M T+ (b) 2 212

M M T⎡ ⎤+ +⎣ ⎦

(c) [ ]12

M T+ (d) 2 214

M T⎡ ⎤+⎣ ⎦

IES-19. A solid circular shaft is subjected to a bending moment M and twisting moment

T. What is the equivalent twisting moment Te which will produce the same maximum shear stress as the above combination? [IES-1992; 2007]

(a) M2 + T2 (b) M + T (c) +2 2M T (d) M – T IES-20. A shaft is subjected to fluctuating loads for which the normal torque (T) and

bending moment (M) are 1000 N-m and 500 N-m respectively. If the combined shock and fatigue factor for bending is 1.5 and combined shock and fatigue factor for torsion is 2, then the equivalent twisting moment for the shaft is:

[IES-1994] (a) 2000N-m (b) 2050N-m (c) 2100N-m (d) 2136 N-m IES-21. A member is subjected to the combined action of bending moment 400 Nm and

torque 300 Nm. What respectively are the equivalent bending moment and equivalent torque? [IES-1994; 2004]

(a) 450 Nm and 500 Nm (b) 900 Nm and 350 Nm (c) 900 Nm and 500 Nm (d) 400 Nm and 500 Nm IES-22. A shaft was initially subjected to bending moment and then was subjected to

torsion. If the magnitude of bending moment is found to be the same as that of the torque, then the ratio of maximum bending stress to shear stress would be:

[IES-1993] (a) 0.25 (b) 0.50 (c) 2.0 (d) 4.0 IES-23. A shaft is subjected to simultaneous action of a torque T, bending moment M

and an axial thrust F. Which one of the following statements is correct for this situation? [IES-2004]



(a) One extreme end of the vertical diametral fibre is subjected to maximum compressive stress only

(b) The opposite extreme end of the vertical diametral fibre is subjected to tensile/compressive stress only

(c) Every point on the surface of the shaft is subjected to maximum shear stress only (d) Axial longitudinal fibre of the shaft is subjected to compressive stress only IES-24. For obtaining the

maximum shear stress induced in the shaft shown in the given figure, the torque should be equal to

( )1

2 22

12 22

2

(a) (b)

(c)2

(d)2

T Wl T

wLWl

wLWl T

+

⎡ ⎤⎛ ⎞+⎢ ⎥⎜ ⎟⎝ ⎠⎢ ⎥⎣ ⎦

⎡ ⎤⎧ ⎫⎢ ⎥+ +⎨ ⎬⎢ ⎥⎩ ⎭⎣ ⎦

[IES-1999] IES-25. Bending moment M and torque is applied on a solid circular shaft. If the

maximum bending stress equals to maximum shear stress developed, them M is equal to: [IES-1992]

(a) (b) (c) 2 (d) 42T T T T

IES-26. A circular shaft is subjected to the combined action of bending, twisting and

direct axial loading. The maximum bending stress σ, maximum shearing force 3σ and a uniform axial stress σ(compressive) are produced. The maximum

compressive normal stress produced in the shaft will be: [IES-1998] (a) 3 σ (b) 2 σ (c) σ (d) Zero IES-27. Which one of the following statements is correct? Shafts used in heavy duty

speed reducers are generally subjected to: [IES-2004] (a) Bending stress only (b) Shearing stress only (c) Combined bending and shearing stresses (d) Bending, shearing and axial thrust simultaneously

Comparison of Solid and Hollow Shafts IES-28. The ratio of torque carrying capacity of a solid shaft to that of a hollow shaft is

given by: [IES-2008] ( ) ( ) 14 4 4 4(a) 1 K (b) 1 K (c)K (d)1/ K

−− −

Where K = i

o

DD

; Di = Inside diameter of hollow shaft and Do = Outside diameter of hollow

shaft. Shaft material is the same. IES-29. A hollow shaft of outer dia 40 mm and inner dia of 20 mm is to be replaced by a

solid shaft to transmit the same torque at the same maximum stress. What should be the diameter of the solid shaft? [IES 2007]



(a) 30 mm (b) 35 mm (c) 10× (60)1/3 mm (d) 10× (20)1/3 mm IES-30. The diameter of a solid shaft is D. The inside and outside diameters of a hollow

shaft of same material and length are 3

D and

32D

respectively. What is the

ratio of the weight of the hollow shaft to that of the solid shaft? [IES 2007] (a) 1:1 (b) 1: 3 (c) 1:2 (d) 1:3 IES-31. What is the maximum torque transmitted by a hollow shaft of external radius R

and internal radius r? [IES-2006]

(a) ( )3 3

16 sR r fπ − (b) ( )4 4

2 sR r fRπ − (c) ( )4 4

8 sR r fRπ − (d)

4 4

32 sR r f

Rπ ⎛ ⎞−⎜ ⎟⎝ ⎠

( sf = maximum shear stress in the shaft material) IES-32. A hollow shaft of the same cross-sectional area and material as that of a solid

shaft transmits: [IES-2005] (a) Same torque (b) Lesser torque (c) More torque (d) Cannot be predicted without more data IES-33. The outside diameter of a hollow shaft is twice its inside diameter. The ratio of

its torque carrying capacity to that of a solid shaft of the same material and the same outside diameter is: [GATE-1993; IES-2001]

(a) 1516

(b) 34

(c) 12

(d) 1

16

IES-34. Two hollow shafts of the same material have the same length and outside

diameter. Shaft 1 has internal diameter equal to one-third of the outer diameter and shaft 2 has internal diameter equal to half of the outer diameter. If both the shafts are subjected to the same torque, the ratio of their twists

1 2/θ θ will be equal to: [IES-1998] (a) 16/81 (b) 8/27 (c) 19/27 (d) 243/256 IES-35. Maximum shear stress in a solid shaft of diameter D and length L twisted

through an angle θ is τ. A hollow shaft of same material and length having outside and inside diameters of D and D/2 respectively is also twisted through the same angle of twist θ. The value of maximum shear stress in the hollow shaft will be: [IES-1994; 1997]

( ) ( ) ( ) ( )16 8 4a b c d 15 7 3

τ τ τ τ

IES-36. A solid shaft of diameter 'D' carries a twisting moment that develops maximum

shear stress τ. If the shaft is replaced by a hollow one of outside diameter 'D' and inside diameter D/2, then the maximum shear stress will be: [IES-1994]

(a) 1.067 τ (b) 1.143 τ (c) 1.333 τ (d) 2 τ IES-37. A solid shaft of diameter 100 mm, length 1000 mm is subjected to a twisting

moment 'T’ The maximum shear stress developed in the shaft is 60 N/mm2. A hole of 50 mm diameter is now drilled throughout the length of the shaft. To develop a maximum shear stress of 60 N/mm2 in the hollow shaft, the torque 'T’ must be reduced by: [IES-1998, 2012]

(a) T/4 (b) T/8 (c) T/12 (d)T/16 IES-38. Assertion (A): A hollow shaft will transmit a greater torque than a solid shaft of

the same weight and same material. [IES-1994]



Reason (R): The average shear stress in the hollow shaft is smaller than the average shear stress in the solid shaft.

(a) Both A and R are individually true and R is the correct explanation of A (b) Both A and R are individually true but R is NOT the correct explanation of A (c) A is true but R is false (d) A is false but R is true IES-39. A hollow shaft is subjected to torsion. The shear stress variation in the shaft

along the radius is given by: [IES-1996]

Shafts in Series IES-40. What is the total angle of

twist of the stepped shaft subject to torque T shown in figure given above?

(a) 4

16 lTGdπ

(b) 4

38 lTGdπ

(c) 4

64 lTGdπ

(d) 4

66 lTGdπ

[IES-2005]

Shafts in Parallel IES-41. For the two shafts connected in parallel, find which statement is true? (a) Torque in each shaft is the same [IES-1992, 2011] (b) Shear stress in each shaft is the same (c) Angle of twist of each shaft is the same (d) Torsional stiffness of each shaft is the same IES-42. A circular section rod ABC is fixed at ends A and C. It is subjected to torque T

at B. AB = BC = L and the polar moment of inertia of portions AB and BC are 2 J and J respectively. If G is the modulus of rigidity, what is the angle of twist at point B? [IES-2005]

(a) 3TLGJ

(b) 2TLGJ

(c) TLGJ

(d) 2TLGJ

IES-43. A solid circular rod AB of diameter D and length L is fixed at both ends. A torque T is applied at a section X such that AX = L/4 and BX = 3L/4. What is the maximum shear stress developed in the rod? [IES-2004]

(a) 3

16TDπ

(b) 3

12TDπ

(c) 3

8TDπ

(d) 3

4TDπ



IES-44. Two shafts are shown in the above figure. These two shafts will be torsionally equivalent to each other if their

(a) Polar moment of inertias are the same

(b) Total angle of twists are the same

(c) Lengths are the same (d) Strain energies are the

same

[IES-1998]


Torsion Equation IAS-1. Assertion (A): In theory of torsion, shearing strains increase radically away

from the longitudinal axis of the bar. [IAS-2001] Reason (R): Plane transverse sections before loading remain plane after the

torque is applied. (a) Both A and R are individually true and R is the correct explanation of A (b) Both A and R are individually true but R is NOT the correct explanation of A (c) A is true but R is false (d) A is false but R is true IAS-2. The shear stress at a point in a shaft subjected to a torque is: [IAS-1995] (a) Directly proportional to the polar moment of inertia and to the distance of the point

form the axis (b) Directly proportional to the applied torque and inversely proportional to the polar

moment of inertia. (c) Directly proportional to the applied torque and polar moment of inertia (d) inversely proportional to the applied torque and the polar moment of inertia IAS-3. If two shafts of the same length, one of which is hollow, transmit equal torque

and have equal maximum stress, then they should have equal. [IAS-1994] (a) Polar moment of inertia (b) Polar modulus of section (c) Polar moment of inertia (d) Angle of twist

Hollow Circular Shafts IAS-4. A hollow circular shaft having outside diameter 'D' and inside diameter ’d’

subjected to a constant twisting moment 'T' along its length. If the maximum shear stress produced in the shaft is sσ then the twisting moment 'T' is given by: [IAS-1999]

(a)4 4

48 sD d

Dπ σ −

(b)4 4

416 sD d

Dπ σ −

(c) 4 4

432 sD d

Dπ σ −

(d)4 4

464 sD d

Dπ σ −

Torsional Rigidity IAS-5. Match List-I with List-II and select the correct answer using the codes given

below the lists: [IAS-1996] List-I (Mechanical Properties) List-II ( Characteristics) A. Torsional rigidity 1. Product of young's modulus and second

moment of area about the plane of bending



B. Modulus of resilience 2. Strain energy per unit volume C. Bauschinger effect 3. Torque unit angle of twist D. Flexural rigidity 4. Loss of mechanical energy due to local

yielding Codes: A B C D A B C D (a) 1 3 4 2 (b) 3 2 4 1 (c) 2 4 1 3 (d) 3 1 4 2 IAS-6. Assertion (A): Angle of twist per unit length of a uniform diameter shaft

depends upon its torsional rigidity. [IAS-2004] Reason (R): The shafts are subjected to torque only. (a) Both A and R are individually true and R is the correct explanation of A (b) Both A and R are individually true but R is NOT the correct explanation of A (c) A is true but R is false (d) A is false but R is true

Combined Bending and Torsion IAS-7. A shaft is subjected to a bending moment M = 400 N.m alld torque T = 300 N.m

The equivalent bending moment is: [IAS-2002] (a) 900 N.m (b) 700 N.m (c) 500 N.m (d) 450 N.m

Comparison of Solid and Hollow Shafts IAS-8. A hollow shaft of length L is fixed at its both ends. It is subjected to torque T at

a distance of 3L

from one end. What is the reaction torque at the other end of

the shaft? [IAS-2007]

(a) 23T

(b) 2T

(c) 3T

(d) 4T

IAS-9. A solid shaft of diameter d is replaced by a hollow shaft of the same material

and length. The outside diameter of hollow shaft 2

3d

while the inside diameter

is 3

d. What is the ratio of the torsional stiffness of the hollow shaft to that of

the solid shaft? [IAS-2007]

(a) 23

(b) 35

(c) 53

(d) 2

IAS-10. Two steel shafts, one solid of diameter D and the other hollow of outside

diameter D and inside diameter D/2, are twisted to the same angle of twist per unit length. The ratio of maximum shear stress in solid shaft to that in the hollow shaft is: [IAS-1998]

(a) 49τ (b)

87τ (c)

1615

τ (d) τ

Shafts in Series IAS-11. Two shafts having the same length and material are joined in series. If the

ratio of the diameter of the first shaft to that of the second shaft is 2, then the ratio of the angle of twist of the first shaft to that of the second shaft is:

[IAS-1995; 2003] (a) 16 (b) 8 (c) 4 (d) 2



IAS-12. A circular shaft fixed at A has diameter D for half of its length and diameter D/2 over the other half. What is the rotation of C relative of B if the rotation of B relative to A is 0.1 radian? [IAS-1994]

(a) 0.4 radian (b) 0.8 radian (c) 1.6 radian (d) 3.2 radian

(T, L and C remaining same in both cases)

Shafts in Parallel IAS-13. A stepped solid circular shaft shown in the given figure is built-in at its ends

and is subjected to a torque To at the shoulder section. The ratio of reactive torque T1 and T2 at the ends is (J1 and J2 are polar moments of inertia):

(a) 2 2

1 1

J lJ l××

(b) 2 1

1 2

J lJ l××

(c) 1 2

2 1

J lJ l××

(d) 1 1

2 2

J lJ l××

[IAS-2001]

IAS-14. Steel shaft and brass shaft of same length and diameter are connected by a flange coupling. The assembly is rigidity held at its ends and is twisted by a torque through the coupling. Modulus of rigidity of steel is twice that of brass. If torque of the steel shaft is 500 Nm, then the value of the torque in brass shaft will be: [IAS-2001]

(a) 250 Nm (b) 354 Nm (c) 500 Nm (d) 708 Nm IAS-15. A steel shaft with bult-in ends is subjected to the action of a torque Mt applied

at an intermediate cross-section 'mn' as shown in the given figure. [IAS-1997]

Assertion (A): The magnitude of the twisting moment to which the portion BC

is subjected is +

tM aa b

Reason(R): For geometric compatibility, angle of twist at 'mn' is the same for the portions AB and BC.

(a) Both A and R are individually true and R is the correct explanation of A (b) Both A and R are individually true but R is NOT the correct explanation of A (c) A is true but R is false (d) A is false but R is true IAS-16. A steel shaft of outside diameter 100 mm is solid over one half of its length and

hollow over the other half. Inside diameter of hollow portion is 50 mm. The shaft if held rigidly at two ends and a pulley is mounted at its midsection i.e., at the junction of solid and hollow portions. The shaft is twisted by applying



torque on the pulley. If the torque carried by the solid portion of the shaft is 16000kg-m, then the torque carried by the hollow portion of the shaft will be:

[IAS-1997] (a) 16000 kg-m (b) 15000 kg-m (c) 14000 kg-m (d) 12000 kg-m



OBJECTIVE ANSWERS

GATE-1. Ans. (a) 3

16Td

τπ

=

GATE-2. Ans. (c) ( )3 3 3

16T 16T 16T 240, 240 if diameter doubled d 2d, then 30MPa8d d 2d

τ τπ π π

′ ′= = = = = =

GATE-2(i) Ans. (a)

Maximum shear stress = π 316T

d

Normal stress = 0

GATE-3. Ans. (c) 3

16Td

τπ

= as T & d both are same τ is same

GATE-4. Ans. (c) GATE-4a. Ans. (b) Angular twist at the

free end

1 2

4 4

4 4 4

14

2(2 ) ( )

32 322 16 18

18

LTT L

G d G d

TL TL TLG d G d G d

TLdG

θ θ θ

π π

π π π

πθ

= +

××= +× ×

= + =

⎛ ⎞⇒ = ⎜ ⎟⎝ ⎠

GATE-5. Ans. (c) 3

3

2 N 16T dPower, P T and or T60 16dπ τπτ

π= × = =

3

3d 2 Nor P orP d16 60τπ π α= ×

GATE-5(i) Ans. (c)

TRJτ=

⇒ TRJτ = ×

−π= × × − × × = Ν −4 4 62125 (100 50 ) 10 23.00 k m32 100

GATE-6. Ans. (d) Equivalent torque ( ) 2 2 2 2eT M T 3 4 5kNm= + = + =

GATE-7. Ans. (a) T G Jor T if is const. T JJ L R R

θ τ τ τ α= = =

44

h h

4

DD32 2T J 15

T J 16D32

π

π

⎡ ⎤⎛ ⎞−⎢ ⎥⎜ ⎟⎝ ⎠⎢ ⎥⎣ ⎦= = =

GATE-7(i) Ans. (b)

TR Jτ =

Here, π= −4 4 4J (20 16 )mm ;32

d2d

L L/2

T

θ1 θ2



= =120R 10 mm;2

T = 92.7 N-m;

= =216R 8 mm2

3

11

4 4

TR 92.7 10 10 99.96 MPa 100 MPaJ (20 16 )

32

× ×τ = = = ≈π⎛ ⎞ × −⎜ ⎟

⎝ ⎠

and 3

22

4 4

TR 92.7 10 8 79.96 MPa 80 MPaJ (20 16 )

32

× ×τ = = = ≈π⎛ ⎞ × −⎜ ⎟

⎝ ⎠

GATE-7(ii)Ans. (c) We know that

TR Jτ =

⇒ 1 1 1 2

2 2 2 1

R TR T

JJ

τ= × ×

τ

⇒ τ ⎛ ⎞= × × ⎜ ⎟τ ⎝ ⎠

41 1 1 1

2 1 1 1

R T 2R2R 4T R

⇒ τ= × ×

τ1

2

1 1 162 4

⇒ ττ = 1

2 2

⇒ ττ =2 2

GATE-8. Ans. (b) TLWe know that or T k. [let k tortional stiffness]GJ

θ θ= = =

NO OPMNMN NO OP

MN NO OP

T TT 10 10 10 1.0 radk k k 20 30 60

θ θ θ θ∴ = + + = + + = + + =

GATE-9. Ans. (c) ( )

C C C CA A AAB BC A4 4

A A C C

T L T TT L Tor or or TG J G J 16d 2d

32 32

θ θπ π

= = = =

GATE-10. Ans. (b) The symmetry of the shaft shows that there is no torsion on section AB.

∴ Rotation, θ =11

TLGJ

IES-10(i). Ans. (a)

IES

IES-1. Ans. (d) 3

T r 16TJ d

τπ

×= =

IES-2. Ans. (a) IES-2(i). Ans. (d)

IES-3. Ans. (c) Maximum shear stress = 3

16Tdπ

= 240 MPa = τ

Maximum shear stress developed when diameter is doubled



( )

τ τ⎛ ⎞= = = = =⎜ ⎟π⎝ ⎠π 3 316 1 16T 240 30MPa

8 d 8 82d

IES-4. Ans. (c) 3

3

16T dor T for same material const.16dτπτ τ

π= = =

3 3

3 2 2

1 1

T d 60T d or 8T d 30

α⎛ ⎞ ⎛ ⎞∴ = = =⎜ ⎟ ⎜ ⎟

⎝ ⎠⎝ ⎠

IES-5. Ans. (b) IES-5(i). Ans. (b) IES-5(ii). Ans. (b) IES-6. Ans. (d) IES-6a Ans. (b) IES-7. Ans. (a) IES-8. Ans. (c) IES-9. Ans. (d)

IES-10. Ans. (c) T G GR 1orJ R L L L

τ θ θτ τ= = = ∴ ∞

IES-11. Ans. (d) τ τ= =T JorT

J r r

;2

τ τ ⎡ ⎤= = =⎢ ⎥⎣ ⎦s h h

s hs h

J J Dor r rr r

( )

4

4 4

32

32

π

τ τ τ π= × = ×−

sh

h

DJorJ D d

4 4

1 1 1615251 1

50

τ τ τ ⎛ ⎞= × = × = ⎜ ⎟⎡ ⎤ ⎡ ⎤ ⎝ ⎠⎛ ⎞ ⎛ ⎞− −⎢ ⎥ ⎢ ⎥⎜ ⎟ ⎜ ⎟⎝ ⎠ ⎝ ⎠⎢ ⎥ ⎢ ⎥⎣ ⎦ ⎣ ⎦

dD

IES-12. Ans. (d)

T G T.Lor Q if is const. T J if J is doubled then T is also doubled.J L R G.J

θ τ θ α= = =

IES-13. Ans. (d) ( ) ( )Power (P) torque T angular speed ω= ×

( )

( )( )3 3 3

1 T 1if P is const.T if or T T / 2T 2

16 T / 216T d 1ordd 2d

ωαω ω

σπ π

′ ′= = =′′⎛ ⎞= = =⎜ ⎟′ ⎝ ⎠

IES-14. Ans. (a) 3

3


π= × = =

1/33

32

d 2 N 480 P Por P or d or d16 60 NJ Nτπ π α

π⎛ ⎞= × = ⎜ ⎟⎝ ⎠

IES-15. Ans. (c)

IES-16. Ans. (c) 3

3


π= × = =

3

3d 2 Nor P orP d16 60τπ π α= ×

IES-17. Ans. (d) IES-18. Ans. (b)

IES-19. Ans. (c) Te = 22 TM +

IES-20. Ans. (d) ( ) ( )2 21.5 500 2 1000 2136 Nm= × + × =eqT

IES-21. Ans. (a) ( )2 2 2 2

eM M T 400 400 300Equivalent Bending Moment M 450N.m

2 2+ + + += = =



( ) 2 2 2 2eEquivalent torque T M T 400 300 500N.m= + = + =

IES-22. Ans. (c) Use equivalent bending moment formula, 1st case: Equivalent bending moment (Me) = M

2nd case: Equivalent bending moment (Me) = 2 20 0

2 2T T+ + =

IES-23. Ans. (a)

IES-24. Ans. (d) Bending Moment, M = 2

2+ wLWl

IES-25. Ans. (a) 3

32 Md

σπ×= and 3

16Td

τπ

=

IES-26. Ans. (a) Maximum normal stress = bending stress σ + axial stress (σ) = 2 σ We have to take maximum bending stress σ is (compressive)

The maximum compressive normal stress = 2

2

2 2σ σ τ⎛ ⎞− +⎜ ⎟

⎝ ⎠b b

xy

( )2

22 2 3 32 2σ σ σ σ− −⎛ ⎞= − + = −⎜ ⎟

⎝ ⎠

IES-27. Ans. (c) IES-28. Ans. (b) τ should be same for both hollow and solid shaft

( )( )

144s s o sh i

4 44 4 4 h h oo io o i

14s

h

T T D TT D1

T T DD DD D D32 32

T1 k

T

−

−

⎛ ⎞⎛ ⎞⎜ ⎟= ⇒ = ⇒ = − ⎜ ⎟π π ⎜ ⎟− ⎝ ⎠− ⎝ ⎠

∴ −

IES-29. Ans. (c) Section modules will be same

H

H

JR

= s

s

JR

or

240

)2040(64

44 −π

= 64π ×

2

4

dd

or, d3 = (10)3 ×60 or d = 10 3 60 mm

IES-30. Ans. (a) S

H

WW

= 1

4

334

42

22

=×××

×××⎟⎟⎠

⎞⎜⎜⎝

⎛−

gLD

gLDD

ρπ

ρπ

IES-31. Ans. (b) ( )

( )4 4

4 4ss s s

R rfT J 2or T f f R r .f .J R R R 2R

ππ−

= = × = × = −

IES-32. Ans. (c) 2

H H

2S H

T Dn 1 , Where nT dn n 1

+= =−

IES-33. Ans. (a) T G Jor T if is const. T JJ L R R

θ τ τ τ α= = =

44

h h

4

DD32 2T J 15

T J 16D32

π

π

⎡ ⎤⎛ ⎞−⎢ ⎥⎜ ⎟⎝ ⎠⎢ ⎥⎣ ⎦= = =



IES-34. Ans. (d)

44 1

11

442 1

1

21 243256

3

ddQQJ Q dd

⎛ ⎞− ⎜ ⎟⎝ ⎠∞ ∴ = =⎛ ⎞− ⎜ ⎟⎝ ⎠

IES-35. Ans. (d) T G G.R.or if is const. RJ L R L

θ τ θτ θ τ α= = = and outer diameter is same in both

the cases. Note: Required torque will be different.

IES-36. Ans. (a) T G TR 1or if T is const.J L R J J

θ τ τ τ α= = =

4

h4

h 4

J D 16 1.06666J 15DD

2

ττ

= = = =⎛ ⎞− ⎜ ⎟⎝ ⎠

IES-37. Ans. (d) ( )43 4

16 32( / 2) 15or16/ 2

sTr T T d TJ d Td d

τπ

′ ′= = = =

−

1Reduction

16∴ =

IES-38. Ans. (a) IES-39. Ans. (c)

IES-40. Ans. (d) ( )

[ ]1 2 4 4 44

T 2l T l Tl 66Tl64 2d Gd GdG 2dG. 3232

θ θ θ ππ× ×= + = + = + =

× ×

IES-41. Ans. (c) IES-42. Ans. (a)

AB BCθ θ=

BC.ABAB BC

AB BC BC

B AB

T LT Lor or T 2T

G.2J G.JT T T or T T / 3

T L TLor Q Q .3 GJ 3GJ

= =

+ = =

= = =

IES-43. Ans. (b)

AX XB A B

BA.

A B A

Amax 4

3

& T T T3LTT L / 4 4or

GJ GJ3Tor T 3T or T ,4

316 T16T 12T4D3 D3D

θ θ

τπ ππ

= + =

×=

= =

× ×= = =

IES-44. Ans. (b)

IAS IAS-1. Ans. (b)

IAS-2. Ans. (b) RJ

T τ=

IAS-3. Ans. (b) RJ

T τ= Here T & τ are same, so JR

should be same i.e. polar modulus of section

will be same.



IAS-4. Ans. (b) ( ) ( )4 4 4 4

s

s

D d D dT G J 32gives TDJ L R R 16 D2

πσθ τ τ π σ× − −

= = = = =

IAS-5. Ans. (b) IAS-6. Ans. (c)

IAS-7. Ans. (d) 2 2 2 2400 400 300 450

2 2M M TMe Nm+ + + += = =

IAS-8. Ans. (c)

IAS-9. Ans. (c) Torsional stiffness =

4 4

4

232 3 3 5

3.32

H

S

d d

KT GJ orL K d

π

πθ

⎧ ⎫⎛ ⎞ ⎛ ⎞⎪ ⎪−⎨ ⎬⎜ ⎟ ⎜ ⎟⎝ ⎠ ⎝ ⎠⎪ ⎪⎛ ⎞ ⎩ ⎭= = =⎜ ⎟

⎝ ⎠

IAS-10. Ans. (d) T G G RorJ R L L

τ θ θτ= = = as outside diameter of both the shaft is D so τ is

same for both the cases.

IAS-11. Ans. (a) Angle of twist is proportional to 4

1 1J d∞

IAS-12. Ans. (c) L

GJT θ= or

J1∞θ or 4

1d

∞θ 32

4dJ π=∵

Here ( )44

2/1.0 dd=θ

or 6.1=θ radian.

IAS-13. Ans. (c) 1 1 2 2 1 1 21 2

1 2 2 2 1

or orT l T l T J lGJ GJ T J l

θ θ⎛ ⎞

= = = ×⎜ ⎟⎝ ⎠

IAS-14. Ans. (a)

1 21 250 Nm2 2

s s b b s b b b sb

s s b b s b s s

T l T l T T T G Tor or or or TG J G J G G T G

θ θ= = = = = = =

IAS-15. Ans. (a)

IAS-16. Ans.(b) ( )

( )

4 4

s H Hs H H S

4s H s

100 50T L T L J 32or or T T 16000 15000kgmGJ GJ J 100

32

π

θ θ π

−= = = × = × =




Conventional Question IES 2010 Q. A hollow steel rod 200 mm long is to be used as torsional spring. The ratio of

inside to outside diameter is 1 : 2. The required stiffness of this spring is 100 N.m /degree.

Determine the outside diameter of the rod. Value of G is 4 28 10 N/mm× . [10 Marks] Ans. Length of a hollow steel rod = 200mm Ratio of inside to outside diameter = 1 : 2 Stiffness of torsional spring = 100 Nm /degree. = 5729.578 N m/rad Rigidity of modulus (G) = 4 28 10 N / mm× Find outside diameter of rod : - We know that

T G. = J L

θ Where T = Torque

T N MStiffnessθ rad

−⎛ ⎞= ⎜ ⎟⎝ ⎠

J = polar moment Stiffness = T G.J =

Lθ θ = twist angle in rad

L = length of rod. 2 1d 2d=

( )( )

−

π ×

π ×

π × ×

× × π× × ×

× ×× × π×

×

×

∵

4 42 1

4 4 11 1

2

41

4 6 241

4110

31

1

2

J = d - d32

d 1J = 16d - d = 32 d 2

J = d 1532

8 10 10 N / m5729.578Nm / rad = d 150.2 32

5729.578 .2 32 = d8 10 15

d = 9.93 10 m.d = 9.93mm.d = 2 9.93 = 19.86 mm Ans.

Conventional Question GATE - 1998 Question: A component used in the Mars pathfinder can be idealized as a circular bar

clamped at its ends. The bar should withstand a torque of 1000 Nm. The component is assembled on earth when the temperature is 30°C. Temperature on Mars at the site of landing is -70°C. The material of the bar has an allowable shear stress of 300 MPa and its young's modulus is 200 GPa. Design the diameter of the bar taking a factor of safety of 1.5 and assuming a coefficient of thermal expansion for the material of the bar as 12 × 10–6/°C.

Answer: Given:



( )

0 0max E m allowable

6 0

6 4

T 1000Nm; t 30 C; t 70 C; 300MPa

E 200GPa; F.O.S. 1.5; 12 10 / CDiameter of the bar,D :Change in length, L L t,where L original length,m.Change in lengthat Mars L 12 10 30 70 12 10 L meters

τα

δ

−

− −

= = = − =

= = = ×

= ∝ Δ =

⎡ ⎤= × × × − − = ×⎣ ⎦

2

44

9 4 8a

22a

max 3

max

Change in length 12 10 LLinear strain 12 10original length L

axial stress E linear strain 200 10 12 10 2.4 10 N / mFrom max imum shear stress equation,we have

16TD 2

where,

σ

στπ

τ

−−

−

×= = = ×

= = × = × × × = ×

⎡ ⎤⎛ ⎞⎛ ⎞= +⎢ ⎥⎜ ⎟ ⎜ ⎟⎝ ⎠ ⎝ ⎠⎢ ⎥⎣ ⎦

( )

allowable

2216 8

3

83

1/3

8

300 200MPaF.O.S 1.5

Substituting the values, we get

16 10004 10 1.2 10D

16 1000or 1.6 10D

16 1000or D 0.03169 m 31.69 mm1.6 10

τ

π

π

π

= = =

×⎛ ⎞× = + ×⎜ ⎟⎝ ⎠

× = ×

×⎛ ⎞= = =⎜ ⎟× ×⎝ ⎠

Conventional Question IES-2009 Q. In a torsion test, the specimen is a hollow shaft with 50 mm external and 30 mm

internal diameter. An applied torque of 1.6 kN-m is found to produce an angular twist of 0.4º measured on a length of 0.2 m of the shaft. The Young’s modulus of elasticity obtained from a tensile test has been found to be 200 GPa. Find the values of

(i) Modulus of rigidity. (ii) Poisson’s ratio. [10-Marks] Ans. We have

T G ......... (i)J r L

τ θ= =

Where J = polar moment of inertia

( )( )

4 4

4 4 12

7

3

J = D d32

50 30 10325.338 10

T 1.6 kN m 1.6 10 N-m= 0.4º

l = 0.2 m

−

−

π −

π= − ×

= ×

= − = ×θ

9 2E = 200 × 10 N/m

T GFrom equation (i) J L

θ=

3

7

3

7

G 0.41.6 10 1800.25.338 10

1.6 0.2 10 180 G = 0.4 5.338 10

85.92 GPa

−

−

π⎡ ⎤× ×⎢ ⎥× ⎣ ⎦=×

× × ×⇒

× π × ×=



We also have

Conventional Question IAS - 1996 Question: A solid circular uniformly tapered shaft of length I, with a small angle of

taper is subjected to a torque T. The diameter at the two ends of the shaft are D and 1.2 D. Determine the error introduced of its angular twist for a given length is determined on the uniform mean diameter of the shaft.

Answer: For shaft of tapering's section, we have

2 2 2 21 1 2 2 1 1 2 2

3 3 3 31 2 1 2

R R R R D D D D2TL 32TL3G R R 3G D D

θπ π⎡ ⎤ ⎡ ⎤+ + + += =⎢ ⎥ ⎢ ⎥⎣ ⎦ ⎣ ⎦

( ) ( )

( ) ( )[ ]

2 2

1 23 34

4

1.2 1.2 1 132TL D D and D 1.2D3G D 1.2 1

32TL 2.10653G D

π

π

⎡ ⎤+ × += = =⎢ ⎥

×⎢ ⎥⎣ ⎦

= ×

∵

avg

1.2D DNow, D 1.1D2+= =

( )( ) ( )

2

6 4 44

3 1.1D32TL 32TL 3 32TL' 2.0493G 3G 3G D1.1D 1.2 .D

θπ π π

⎡ ⎤∴ = × = × = ×⎢ ⎥

⎢ ⎥⎣ ⎦

' 2.1065 2.049Error 0.0273 or 2.73%2.1065

θ θθ− −= = =

Conventional Question ESE-2008 Question: A hollow shaft and a solid shaft construction of the same material have the

same length and the same outside radius. The inside radius of the hollow shaft is 0.6 times of the outside radius. Both the shafts are subjected to the same torque.

(i) What is the ratio of maximum shear stress in the hollow shaft to that of solid shaft?

(ii) What is the ratio of angle of twist in the hollow shaft to that of solid shaft?

Solution: Using T Gθ= =J R L

τ

Given, Inside radius (r) 0.6 and T

Out side (R)= = =h sT T

(i) τ =( )

h4 4

. . gives ; For hollow shaft ( )

2

τπ

=−

T R T RJ R r

and for solid shaft ( τ s)= 4

.

.2πT R

R

Therefore 4

44 4 4

1 1 1.151 0.6

1

ττ

= = = =− −⎛ ⎞⎟⎜− ⎟⎜ ⎟⎜⎝ ⎠

n

s

RR r r

R

( )E = 2 G (1 + v) 200 = 2 × 85.92 1 v 1 + v = 1.164 v = 0.164

∴ +

⇒⇒



(ii) ( )4 4 4

TL . .= gives GJ . . .

2 2

θ θ θπ π

= =⎛ ⎞⎟⎜− ⎟⎜ ⎟⎜⎝ ⎠

h sT L T Land

G R r G R

4

44 4 4

θ 1 1Therefore 1.15θ 1 0.6

1= = = =

− −⎛ ⎞⎟⎜− ⎟⎜ ⎟⎜⎝ ⎠

h

s

RR r r

R

Conventional Question ESE-2006: Question: Two hollow shafts of same diameter are used to transmit same power. One

shaft is rotating at 1000 rpm while the other at 1200 rpm. What will be the nature and magnitude of the stress on the surfaces of these shafts? Will it be the same in two cases of different? Justify your answer.

Answer: We know power transmitted (P) = Torque (T) ×rotation speed (ω )

And shear stress ( τ ) = ( )4 4

.. 22 π60 32πω

= =⎛ ⎞⎟⎜ −⎟⎜ ⎟⎜⎝ ⎠

DPT R PRNJ J D d

Therefore τ α 1N

as P, D and d are constant.

So the shaft rotating at 1000 rpm will experience greater stress then 1200 rpm shaft. Conventional Question ESE-2002 Question: A 5 cm diameter solid shaft is welded to a flat plate by 1 cm filled weld. What

will be the maximum torque that the welded joint can sustain if the permissible shear stress in the weld material is not to exceed 8 kN/cm2? Deduce the expression for the shear stress at the throat from the basic theory.

Answer: Consider a circular shaft connected to a plate by means of a fillet joint as shown in figure. If the shaft is subjected to a torque, shear stress develops in the weld. Assuming that the weld thickness is very small compared to the diameter of the shaft, the maximum shear stress occurs in the throat area. Thus, for a given torque the maximum shear stress in the weld is

max2dT t

Jτ

⎛ ⎞⎟⎜ + ⎟⎜ ⎟⎜⎝ ⎠=

Where T = Torque applied. d = outer diameter of the shaft t = throat thickness J = polar moment of area of the throat

section

= ( )4 4 3232 4

d t d d tπ π⎡ ⎤+ − = ×⎢ ⎥⎣ ⎦

[As t <<d] then max3

2

4

dT

d tτ

π= = 2

2π

Ttd



( )π π

2 6 2max 4 2

2 2 6max

Given d = 5 cm = 0.05 m & t = 1cm = 0.1 m

80008 / 80 80 10 /10

0.05 0.01 80 10 3.1422 2

NkN cm MPa N mm

d tT kNm

τ

τ

−= = = = ×

× × × ×∴ = = =

Conventional Question ESE-2000 Question: The ratio of inside to outside diameter of a hollow shaft is 0.6. If there is a

solid shaft with same torsional strength, what is the ratio of the outside diameter of hollow shaft to the diameter of the equivalent solid shaft.

Answer: Let D = external diameter of hollow shaft So d = 0.6D internal diameter of hollow shaft And Ds=diameter of solid shaft From torsion equation

( )

π

π3 2

π Dπ D

4 4

4

334

34

{ ( 0 . 6 ) }3 2, f o r h o l lo w s h a f t

/ 2

J T = f o r s o l id s h a f tR

2

{1 ( 0 . 6 ) }1 6 1 6

1, 1 . 0 7 21 ( 0 . 6 )

s

s

s

s

TJ R

D DJo r TR D

Da n d J

D

Do rD

τ

ττ

τ

τ τ

=

−= = ×

= ×

− =

= =−

Conventional Question ESE-2001 Question: A cantilever tube of length 120 mm is subjected to an axial tension P = 9.0 kN,

A torsional moment T = 72.0 Nm and a pending Load F = 1.75 kN at the free end. The material is aluminum alloy with an yield strength 276 MPa. Find the thickness of the tube limiting the outside diameter to 50 mm so as to ensure a factor of safety of 4.

Answer: 3 ππR3

Polar moment of inertia (J) =24D tt =



π π π

σπ π

σ

3 2 2

1

2

T.R 2 2 72 18335 or, =2 (0.050)2

49000 9000 57296Direct stress ( )

(0.050)

2Maximum bending stress ( ) [ 2 ]

1750

T TD TD TJ R J J tD t D t t

PA dt t t

dMMy Md J II I J

ττ

×= = = = = =

× ××

= = = =

= = = =

×=

( )

π

σ σ σ

σ σσ

3

b 1 2

2 2 2 62b

1

0.120 0.050 4 106952(0.050)

164248Total longitudinal stress ( )

Maximum principal stress

164248 164248 18335 276 102 2 2 2 4

, 2

b

tt

t

t t t

or t

τ

× ×=

×

∴ = + =

⎛ ⎞⎛ ⎞ ⎛ ⎞ ⎛ ⎞ × ⎟⎜⎟ ⎟ ⎟⎜ ⎜ ⎜ ⎟= + + = + + =⎟ ⎟ ⎟ ⎜⎜ ⎜ ⎜ ⎟⎟ ⎟ ⎟ ⎜⎟ ⎜ ⎜⎜ ⎟⎜⎝ ⎠ ⎝ ⎠⎝ ⎠ ⎝ ⎠

= 3.4 10 2.4m mm−× =

Conventional Question ESE-2000 & ESE 2001 Question: A hollow shaft of diameter ratio 3/8 required to transmit 600 kW at 110 rpm,

the maximum torque being 20% greater than the mean. The shear stress is not to exceed 63 MPa and the twist in a length of 3 m not to exceed 1.4 degrees. Determine the diameter of the shaft. Assume modulus of rigidity for the shaft material as 84 GN/m2.

Answer: Let d = internal diameter of the hollow shaft And D = external diameter of the hollow shaft (given) d = 3/8 D = 0.375D Power (P)= 600 kW, speed (N) =110 rpm, Shear stress( τ )= 63 MPa. Angle of twist (θ

)=1.4°, Length ( ) =3m , modulus of rigidity (G) = 84GPa

We know that, (P) = T. ω= T. 2πN60

[T is average torque]

or T= 602π

PN×

= 360 (600 10 ) 52087Nm

2 π×110× ×

=×

max 1.2 1.2 52087 =62504 Nm∴ = × = ×T T First we consider that shear stress is not to exceed 63 MPa

From torsion equation τ

=TJ R

4 46

. .2

π 62504(0.375 )32 2 (63 10 )

0.1727 172.7 ( )

τ τ= =

×⎡ ⎤− =⎢ ⎥⎣ ⎦ × ×= = −−−−

T R T Dor J

Dor D D

or D m mm i

0 17 1.4Second we consider angle of twist is not exceed 1.4 radian180×

=



4 4

9

T θFrom torsion equation

θ

62504 3(0.375 )π 1.532 (84 10 )180

0.1755 175.5 ( )

π

=

=

×⎡ ⎤− =⎢ ⎥⎣ ⎦ ⎛ ⎞× ⎟⎜× ⎟⎜ ⎟⎜⎝ ⎠

= = −−−−

GJ

T GorJ

or D D

or D m mm ii

both the condition will satisfy if greater of the two value is adopted

so D=175.5 mmSo

Conventional Question ESE-1997 Question: Determine the torsional stiffness of a hollow shaft of length L and having

outside diameter equal to 1.5 times inside diameter d. The shear modulus of the material is G.

Answer: Outside diameter (D) =1.5 d

Polar modulus of the shaft (J) = ( )4 4 4 4π π (1.5 1)32 32

D d d− = −

π 4 44

TWe know that J

. (1.5 1) 0.432

GR L

G dG J G dor TL L L

τ θ

θθ θ

= =

−= = =

Conventional Question AMIE-1996 Question: The maximum normal stress and the maximum shear stress analysed for a

shaft of 150 mm diameter under combined bending and torsion, were found to be 120 MN/m2 and 80 MN/m2 respectively. Find the bending moment and torque to which the shaft is subjected.

If the maximum shear stress be limited to 100 MN/m2, find by how much the torque can be increased if the bending moment is kept constant.

Answer: Given: 2 2max max120MN / m ; 80MN / m ;d 150mm 0.15mσ τ= = = =

Part 1: M; T− We know that for combined bending and torsion, we have the following expressions:

( )

( )

2 2max 3

2 2max 3

16 M M T id

16and M T iid

σπ

τπ

⎡ ⎤= + + − − −⎣ ⎦

⎡ ⎤= + − − − −⎣ ⎦

( )

( )

( )( )

( ) ( )

2 23

2 23

32 2

Substituting the given values in the above equations, we have16120 M M T iii0.151680 M T iv0.15

80 0.15or M T 0.053 v

16

π

π

π

⎡ ⎤= + + − − − − − −⎣ ⎦×

⎡ ⎤= + − − − − − − − − −⎣ ⎦×

× ×+ = = − − − − − −



( )

( ) [ ]3

Substituting this values in equation iii ,we get16120 M 0.0530.150

M 0.0265MNm

π= +

×

∴ =

( )( )2 2

Substituting for M in equation v ,we have

0.0265 T 0.053

or T 0.0459MNm

+ =

=

( )

2maxPart II : [ 100MN / m ]

Increase in torque :Bending moment M to be kept cons tan t 0.0265MNm

τ =

=

∵

( ) ( )23

2 2 100 0.15or 0.0265 T 0.004391

16π⎡ ⎤× ×

⎢ ⎥+ = =⎢ ⎥⎣ ⎦

T 0.0607 MNm

The increased torque 0.0607 0.0459 0.0148MNm∴ =∴ = − =

Conventional Question ESE-1996 Question: A solid shaft is to transmit 300 kW at 120 rpm. If the shear stress is not to

exceed 100 MPa, Find the diameter of the shaft, What percent saving in weight would be obtained if this shaft were replaced by a hollow one whose internal diameter equals 0.6 of the external diameter, the length, material and maximum allowable shear stress being the same?

Answer: Given P= 300 kW, N = 120 rpm, τ =100 MPa, 0.6H Hd D= Diameter of solid shaft, Ds:

We know that P = 2π

60 1000NT

× or 300 =

2π 120 or T=23873 Nm60 1000× ××

T

We know that τ

=TJ R

or, T=.τ JR

or, 23873 =

6 4π100 1032

2

× × s

s

D

D

or, Ds= 0.1067 m =106.7mm Percentage saving in weight: H sT T=



( )π

π

4 4 4 43 3

343

H

S

2 2 22 2

22

{ } (0 .6 ), ,

106 .7, 111 .8 m m1 0.64(1 0 .6 )

WA ga in W

(1 0 .6 ) 111 .84 1106 .7

4

H s

H H H Hs s

H H

sH

H H H H

s s s s

H HH H

s ss

J JR R

D d D Dor D or DD D

Dor D

A L g AA L g A

D dA DA DD

τ τ

ρρ

⎛ ⎞ ⎛ ⎞× ×⎟ ⎟⎜ ⎜=⎟ ⎟⎜ ⎜⎟ ⎟⎜ ⎜⎝ ⎠ ⎝ ⎠

− −= =

= = =−−

= =

− ⎛ ⎞− ⎟⎜= = = −⎟⎜ ⎟⎜⎝ ⎠( )2

H

s

0 .6 0 .702

WP ercen tage sav ings in w e igh t = 1 - 100W

= (1-0 .702)×100 = 29 .8%

=

⎛ ⎞⎟⎜ ⎟∴ ×⎜ ⎟⎜ ⎟⎜⎝ ⎠


10. Thin Cylinder

Theory at a Glance (for IES, GATE, PSU) 1. Thin Rings Uniformly distributed loading (radial) may be due to

either

• Internal pressure or external pressure

• Centrifugal force as in the case of a rotating ring

Case-I: Internal pressure or external pressure

• s = qr Where q = Intensity of loading in kg/cm of Oce

r = Mean centreline of radius s = circumferential tension or hoop’s

tension (Radial loading ducted outward)

• Unit stress, σ = =s qrA A

• Circumferential strain, Ec

qrAE

σ∈ = =

• Diametral strain, (∈d ) = Circumferential strain, (∈c )

Case-II: Centrifugal force

• Hoop's Tension, 2 2ω= w rs

g Where w = wt. per unit length of circumferential element

ω = Angular velocity

• Radial loading, q =2ω= w rs

r g

• Hoop's stress, 2 2.σ ω= =s w rA Ag

2. Thin Walled Pressure Vessels For thin cylinders whose thickness may be considered small compared to their diameter.

iInner dia of the cylinder (d ) 15 or 20wall thickness (t)

>


Chapter-10 Thin Cylinder S K Mondal’s

3. General Formula

1 2

1 2

σ σ+ = pr r t

Where 1σ =Meridional stress at A

2σ =Circumferential / Hoop's stress

P = Intensity of internal gas pressure/ fluid pressure t = Thickness of pressure vessel. 4. Some cases:

• Cylindrical vessel

1 2= 2 4 2

σ σ= = =pr pD pr pDt t t t 1 2 ,r r r⎡ ⎤→∞ =⎣ ⎦

1 2max 2 4 8

σ στ −= = =pr pDt t

• Spherical vessel

1 2 2 4σ σ= = =pr pD

t t [r1 = r2 = r]

• Conical vessel

1 1tan [ ]

2 cospy rt

ασα

= →∞ and 2tan

cospyt

ασα

=

Notes:

• Volume 'V' of the spherical shell, 3V=6π

iD

1/36π

⎛ ⎞⇒ = ⎜ ⎟⎝ ⎠

iVD

• Design of thin cylindrical shells is based on hoop's stress

5. Volumetric Strain (Dilation)

• Rectangular block, 0

x y zV

VΔ =∈ +∈ +∈

• Cylindrical pressure vessel

∈1=Longitudinal strain = [ ]1 2 1 22pr

E E Etσ σμ μ− = −

2∈ =Circumferential strain = [ ]2 1 1 22

σ σμ μ− = −prE E Et

Volumetric Strain, 1 22 [5 4μ] [5 4μ]2 4

Δ =∈ + ∈ = − = −o

V pr pDV Et Et

i.e. ( ) ( ) ( )1 2, 2vVolumetric strain longitudinal strain circumferential strain∈ = ∈ + × ∈

• Spherical vessels

α

α α

α

1σ

2σ2σ



1 2 [1 ]2prEt

μ∈=∈ =∈ = −

0

33 [1 ]2

V prV Et

μΔ = ∈= −

6. Thin cylindrical shell with hemispherical end Condition for no distortion at the junction of cylindrical and hemispherical portion

2

1

12

tt

μμ

−=−

Where, t1= wall thickness of cylindrical portion

t2 = wall thickness of hemispherical portion

7. Alternative method Consider the equilibrium of forces in the z-direction acting on the part cylinder shown in figure.

Force due to internal pressure p acting on area π D2/4 = p. π D2/4

Force due to longitudinal stress sL acting on area π Dt = 1σ π Dt

Equating: p. π D2/4 = 1σ π Dt

or 1 4 2pd pr

t tσ = =

Now consider the equilibrium of forces in the x-direction acting on the sectioned cylinder shown in figure. It is assumed that the

circumferential stress 2σ is constant through the thickness of the

cylinder. Force due to internal pressure p acting on area Dz = pDz

Force due to circumferential stress 2σ acting on area 2tz = 2σ 2tz

Equating: pDz = 2σ 2tz

or 2 2pD pr

t tσ = =





Longitudinal stress GATE-1. A thin cylinder of inner radius 500 mm and thickness 10 mm is subjected to an

internal pressure of 5 MPa. The average circumferential (hoop) stress in MPa is [GATE-2011]

(a) 100 (b) 250 (c) 500 (d) 1000 GATE-2. The maximum principal strain in a thin cylindrical tank, having a radius of 25

cm and wall thickness of 5 mm when subjected to an internal pressure of 1MPa, is (taking Young's modulus as 200 GPa and Poisson's ratio as 0.2) [GATE-1998]

(a) 2.25 × 10–4 (b) 2.25 (c) 2.25 × 10–6 (d) 22.5 GATE-3.A thin walled spherical shell is subjected to an internal pressure. If the radius of

the shell is increased by 1% and the thickness is reduced by 1%, with the internal pressure remaining the same, the percentage change in the circumferential (hoop) stress is [GATE-2012] (a) 0 (b) 1 (c) 1.08 (d) 2.02

GATE-3(i). A long thin walled cylindrical shell, closed at both the ends, is subjected to

an internal pressure. The ratio of the hoop stress (circumferential stress) to longitudinal stress developed in the shell is [GATE-2013] (a) 0.5 (b) 1.0 (c) 2.0 (d) 4.0

Maximum shear stress GATE-4. A thin walled cylindrical vessel of wall thickness, t and diameter d is fitted

with gas to a gauge pressure of p. The maximum shear stress on the vessel wall will then be: [GATE-1999]

(a) (b) (c) (d) 2 4 8

pd pd pd pdt t t t

Statement for Linked Answers and Questions 5 and 6 A cylindrical container of radius R = 1 m, wall thickness 1 mm is filled with water up to a depth of 2 m and suspended along its upper rim. The density of water is 1000 kg/m3 and acceleration due to gravity is 10 m/s2. The self-weight of the cylinder is negligible. The formula for hoop stress in a thin-walled cylinder can be used at all points along the height of the cylindrical container.

[GATE-2008] GATE-5. The axial and circumferential stress ( ), ca σσ experienced by the cylinder wall

at mid-depth (1 m as shown) are (a) (10,10) MPa (b) (5,10) MPa (c) (10,5) MPa (d) (5,5)MPa GATE-6. If the Young's modulus and Poisson's ratio of the container material are 100

GPa and 0.3, respectively, the axial strain in the cylinder wall at mid-depth is:



(a) 2 × 10–5 (b) 6 × 10–5 (c) 7 × 10–5 (d) 1.2 × 10–5

GATE-7. A thin walled cylindrical pressure vessel having a radius of 0.5 m and wall thickness of 25 mm is subjected to an internal pressure of 700 kPa. The hoop stress developed is [CE: GATE-2009]

(a) 14 MPa (b) 1.4 MPa (c) 0.14 MPa (d) 0.014 MPa


Circumferential or hoop stress IES-1. Match List-I with List-II and select the correct answer: [IES-2002] List-I List-II (2-D Stress system loading) (Ratio of principal stresses) A. Thin cylinder under internal pressure 1. 3.0 B. Thin sphere under internal pressure 2. 1.0 C. Shaft subjected to torsion 3. –1.0 4. 2.0 Codes: A B C A B C (a) 4 2 3 (b) 1 3 2 (c) 4 3 2 (d) 1 2 3 IES-2. A thin cylinder of radius r and thickness t when subjected to an internal

hydrostatic pressure P causes a radial displacement u, then the tangential strain caused is: [IES-2002]

(a) dudr

(b) 1 . dur dr

(c) ur

(d) 2ur

IES-3. A thin cylindrical shell is subjected to internal pressure p. The Poisson's ratio

of the material of the shell is 0.3. Due to internal pressure, the shell is subjected to circumferential strain and axial strain. The ratio of circumferential strain to axial strain is: [IES-2001]

(a) 0.425 (b) 2.25 (c) 0.225 (d) 4.25 IES-4. A thin cylindrical shell of diameter d, length ‘l’ and thickness t is subjected to

an internal pressure p. What is the ratio of longitudinal strain to hoop strain in terms of Poisson's ratio (1/m)? [IES-2004]

(a) 2

2 1mm−+

(b) 2

2 1mm−−

(c) 2 1

2m

m−−

(d) 2 2

1mm+−

IES-5. When a thin cylinder of diameter 'd' and thickness 't' is pressurized with an

internal pressure of 'p', (1/m = μ is the Poisson's ratio and E is the modulus of elasticity), then [IES-1998]

(a) The circumferential strain will be equal to 1 1

2 2pdtE m

⎛ ⎞−⎜ ⎟⎝ ⎠

(b) The longitudinal strain will be equal to 11

2 2pdtE m

⎛ ⎞−⎜ ⎟⎝ ⎠



(c) The longitudinal stress will be equal to2pd

t

(d) The ratio of the longitudinal strain to circumferential strain will be equal to 2

2 1mm−−

IES-6. A thin cylinder contains fluid at a pressure of 500 N/m2, the internal diameter of the shell is 0.6 m and the tensile stress in the material is to be limited to 9000 N/m2. The shell must have a minimum wall thickness of nearly [IES-2000]

(a) 9 mm (b) 11 mm (c) 17 mm (d) 21 mm IES-7. A thin cylinder with closed

lids is subjected to internal pressure and supported at the ends as shown in figure.

The state of stress at point X is as represented in

[IES-1999]

IES-8. A thin cylinder with both ends closed is subjected to internal pressure p. The longitudinal stress at the surface has been calculated as σo. Maximum shear stress at the surface will be equal to: [IES-1999]

( ) ( ) ( ) ( )a 2 b 1.5 c d 0.5o o o oσ σ σ σ IES-9. A metal pipe of 1m diameter contains a fluid having a pressure of 10 kgf/cm2. lf

the permissible tensile stress in the metal is 200 kgf/cm2, then the thickness of the metal required for making the pipe would be: [IES-1993]

(a) 5 mm (b) 10 mm (c) 20 mm (d) 25 mm IES-10. Circumferential stress in a cylindrical steel boiler shell under internal

pressure is 80 MPa. Young's modulus of elasticity and Poisson's ratio are respectively 2 × 105 MPa and 0.28. The magnitude of circumferential strain in the boiler shell will be: [IES-1999]

(a) 3.44 × 10–4 (b) 3.84 × 10–4 (c) 4 × 10–4 (d) 4.56 ×10 –4

IES-11. A penstock pipe of 10m diameter carries water under a pressure head of 100 m. If the wall thickness is 9 mm, what is the tensile stress in the pipe wall in MPa?

[IES-2009] (a) 2725 (b) 545·0 (c) 272·5 (d) 1090 IES-12. A water main of 1 m diameter contains water at a pressure head of 100 metres.

The permissible tensile stress in the material of the water main is 25 MPa. What is the minimum thickness of the water main? (Take g = 10 m/ 2s ).

[IES-2009] (a) 10 mm (b) 20mm (c) 50 mm (d) 60 mm



IES-12(i). A seamless pipe of diameter d m is to carry fluid under a pressure of p kN/cm2. The necessary thickness t of metal in cm, if the maximum stress is not to exceed σ kN/cm2, is [IES-2012] ≥ 2 ≥ 1002 ≤ 2 ≤ 1002

Longitudinal stress IES-13. Hoop stress and longitudinal stress in a boiler shell under internal pressure

are 100 MN/m2 and 50 MN/m2 respectively. Young's modulus of elasticity and Poisson's ratio of the shell material are 200 GN/m2 and 0.3 respectively. The hoop strain in boiler shell is: [IES-1995]

(a) 0.425 310−× (b) 0.5 310−× (c) 0.585 310−× (d) 0.75 310−× IES-14. In strain gauge dynamometers, the use of how many active gauge makes the

dynamometer more effective? [IES 2007] (a) Four (b) Three (c) Two (d) One

Volumetric strain IES-15. Circumferential and longitudinal strains in a cylindrical boiler under internal

steam pressure are 1ε and 2ε respectively. Change in volume of the boiler cylinder per unit volume will be: [IES-1993; IAS 2003]

2 21 2 1 2 1 2 1 2(a) 2 (b) (c) 2 (d)ε ε ε ε ε ε ε ε+ +

IES-16. The volumetric strain in case of a thin cylindrical shell of diameter d, thickness

t, subjected to internal pressure p is: [IES-2003; IAS 1997]

(a) ( ). 3 22pdtE

μ− (b) ( ). 4 33pdtE

μ− (c) ( ). 5 44pdtE

μ− (d) ( ). 4 54pdtE

μ−

(Where E = Modulus of elasticity, μ = Poisson's ratio for the shell material)

Spherical Vessel IES-17. For the same internal diameter, wall thickness, material and internal pressure,

the ratio of maximum stress, induced in a thin cylindrical and in a thin spherical pressure vessel will be: [IES-2001]

(a) 2 (b) 1/2 (c) 4 (d) ¼ IES-17(i). What is the safe working pressure for a spherical pressure vessel 1.5 m internal

diameter and 1.5 cm wall thickness, if the maximum allowable tensile stress is 45 MPa?

(a) 0.9 MPa (b) 3.6 MPa (c) 2.7 MPa (d) 1.8 MPa [IES-2013] IES-18. From design point of view, spherical pressure vessels are preferred over

cylindrical pressure vessels because they [IES-1997] (a) Are cost effective in fabrication (b) Have uniform higher circumferential stress (c) Uniform lower circumferential stress (d) Have a larger volume for the same quantity of material used




Circumferential or hoop stress IAS-1. The ratio of circumferential stress to longitudinal stress in a thin cylinder

subjected to internal hydrostatic pressure is: [IAS 1994] (a) 1/2 (b) 1 (c) 2 (d) 4 IAS-2. A thin walled water pipe carries water under a pressure of 2 N/mm2 and

discharges water into a tank. Diameter of the pipe is 25 mm and thickness is 2·5 mm. What is the longitudinal stress induced in the pipe? [IAS-2007]

(a) 0 (b) 2 N/mm2 (c) 5 N/mm2 (d) 10 N/mm2

IAS-3. A thin cylindrical shell of mean diameter 750 mm and wall thickness 10 mm has

its ends rigidly closed by flat steel plates. The shell is subjected to internal fluid pressure of 10 N/mm2 and an axial external pressure P1. If the longitudinal stress in the shell is to be zero, what should be the approximate value of P1? [IAS-2007]

(a) 8 N/mm2 (b) 9 N/mm2 (c) 10 N/mm2 (d) 12 N/mm2

IAS-4. Assertion (A): A thin cylindrical shell is subjected to internal fluid pressure

that induces a 2-D stress state in the material along the longitudinal and circumferential directions. [IAS-2000]

Reason(R): The circumferential stress in the thin cylindrical shell is two times the magnitude of longitudinal stress.

(a) Both A and R are individually true and R is the correct explanation of A (b) Both A and R are individually true but R is NOT the correct explanation of A (c) A is true but R is false (d) A is false but R is true IAS-5. Match List-I (Terms used in thin cylinder stress analysis) with List-II

(Mathematical expressions) and select the correct answer using the codes given below the lists: [IAS-1998]

List-I List-II A. Hoop stress 1. pd/4t B. Maximum shear stress 2. pd/2t C. Longitudinal stress 3. pd/2σ D. Cylinder thickness 4. pd/8t Codes: A B C D A B C D (a) 2 3 1 4 (b) 2 3 4 1 (c) 2 4 3 1 (d) 2 4 1 3

Longitudinal stress IAS-6. Assertion (A): For a thin cylinder under internal pressure, At least three strain

gauges is needed to know the stress state completely at any point on the shell. Reason (R): If the principal stresses directions are not know, the minimum

number of strain gauges needed is three in a biaxial field. [IAS-2001] (a) Both A and R are individually true and R is the correct explanation of A (b) Both A and R are individually true but R is NOT the correct explanation of A (c) A is true but R is false (d) A is false but R is true



Maximum shear stress IAS-7. The maximum shear stress is induced in a thin-walled cylindrical shell having

an internal diameter 'D' and thickness’t’ when subject to an internal pressure 'p' is equal to: [IAS-1996]

(a) pD/t (b) pD/2t (c) pD/4t (d) pD/8t

Volumetric strain IAS-8. Circumferential and longitudinal strains in a cylindrical boiler under internal

steam pressure are 1ε and 2ε respectively. Change in volume of the boiler

cylinder per unit volume will be: [IES-1993; IAS 2003]

2 21 2 1 2 1 2 1 2(a) 2 (b) (c) 2 (d)ε ε ε ε ε ε ε ε+ +

IAS-9. The volumetric strain in case of a thin cylindrical shell of diameter d, thickness

t, subjected to internal pressure p is: [IES-2003; IAS 1997]

(a) ( ). 3 22pdtE

μ− (b) ( ). 4 33pdtE

μ− (c) ( ). 5 44pdtE

μ− (d) ( ). 4 54pdtE

μ−

(Where E = Modulus of elasticity, μ = Poisson's ratio for the shell material) IAS-10. A thin cylinder of diameter ‘d’ and thickness 't' is subjected to an internal

pressure 'p' the change in diameter is (where E is the modulus of elasticity and μ is the Poisson's ratio) [IAS-1998]

(a) 2

(2 )4pdtE

μ− (b)2

(1 )2pdtE

μ+ (c) 2

(2 )pdtE

μ+ (d) 2

(2 )4pdtE

μ+

IAS-11. The percentage change in volume of a thin cylinder under internal pressure having hoop stress = 200 MPa, E = 200 GPa and Poisson's ratio = 0·25 is:

[IAS-2002] (a) 0.40 (b) 0·30 (c) 0·25 (d) 0·20 IAS-12. A round bar of length l, elastic modulus E and Poisson's ratio μ is subjected to

an axial pull 'P'. What would be the change in volume of the bar? [IAS-2007]

(a) (1 2 )

PlEμ−

(b) (1 2 )Pl

Eμ−

(c) PlEμ

(d) PlEμ

IAS-13. If a block of material of length 25 cm. breadth 10 cm and height 5 cm undergoes a volumetric strain of 1/5000, then change in volume will be: [IAS-2000]

(a) 0.50 cm3 (b) 0.25 cm3 (c) 0.20 cm3 (d) 0.75 cm3

OBJECTIVE ANSWERS

GATE-1. Ans. (b) Inner radius (r) = 500 mm Thickness (t) = 10 mm Internal pressure (p) = 5 MPa



Hoop stress, 65 10 500 250

10cpr Pa Mpat

σ × ×= = =

GATE-2. Ans. (a) Circumferential or Hoop stress ( )cpr 1 250 50MPat 5

σ ×= = =

Longitudinal stress ( )lpr 25MPa2t

σ = =

6 6

4c lc 9 9

50 10 25 10e 0.2 2.25 10E E 200 10 200 10σ σμ −× ×= − = − × = ×

× × GATE-3. Ans. (d) GATE-3(i).Ans. (c)

GATE-4. Ans. (d) c lc l

pd pd pd, , Maximum shear stress2t 4t 2 8t

σ σσ σ −= = = =

GATE-5. Ans. (a) Pressure (P) = h ρ g = 1×1000×10 = 10 kPa

Axial Stress ( aσ ) LRgRta22 πρπσ ×=×⇒

or ρσ −

× × ×= = =× 3

1000 10 1 1 10 MPa1 10a

gRLt

Circumferential Stress( cσ )=−

×= =× 3

10 1 10 MPa1 10

PRt

GATE-6. Ans. (c) 533 107

10100103.0

1010010 −

−− ×=×

×−×

=−=EE

caa

σμσε

GATE-7. Ans. (a)

Hoop stress = 2pd

t

−

× × ×= = × =× ×

36

3700 10 2 0.5 14 10 14 MPa

2 25 10

IES

IES-1. Ans. (a) IES-2. Ans. (c)

IES-3. Ans. (d) Circumferential strain, ( )c lc

pre 2E E 2Etσ σμ μ= − = −

Longitudinal strain, ( )cll

pre 1 2E E 2Et

σσ μ μ= − = −

IES-4. Ans. (b) ( )lPrlongitudinal stress2t

σ =

( )c

cl

l

c lc

Prhoop stresst

1 1 1m 2E m E 2 m

11 2m 112mE m E

σ

σσ

σ σ

=

− −∈ −∴ = = =∈ −−−

IES-5. Ans. (d) Ratio of longitudinal strain to circumferential strain

= { }

{ }

1 1 22

1 1 2 12

l c l l

c l l l

mm mm

m m

σ σ σ σ

σ σ σ σ

⎛ ⎞ ⎛ ⎞− −⎜ ⎟ ⎜ ⎟ −⎝ ⎠ ⎝ ⎠= =−⎛ ⎞ ⎛ ⎞− −⎜ ⎟ ⎜ ⎟

⎝ ⎠ ⎝ ⎠



Circumferential strain, ( )c lc

pre 2E E 2Etσ σμ μ= − = −

Longitudinal strain, ( )cll

pre 1 2E E 2Et

σσ μ μ= − = −

IES-6. Ans. (c) IES-7. Ans. (a) Point 'X' is subjected to circumferential and longitudinal stress, i.e. tension on all

faces, but there is no shear stress because vessel is supported freely outside. IES-8. Ans. (d)

2Longitudinal stress hoop stress 2 Max. shear stress

2 2o o o

o oand σ σ σσ σ −= = = =

IES-9. Ans. (d) 10 100 1000Hoop stress 200 2.5

2 2 400pd or or t cm

t t×= = = =×

IES-10. Ans. (a) Circumferential strain = ( )1 21E

σ μσ−

[ ]

1 2

6 45 6

Since circumferential stress 80 MPa and longitudinal stress 40 MPa1Circumferential strain 80 0.28 40 10 3.44 x10

2 10 10

σ σ−

= =

∴ = − × × =× ×

IES-11. Ans. (b) Tensile stress in the pipe wall = Circumferential stress in pipe wall = Pd2t

2

6 2 23

Where, P gH 980000N / m980000 10Tensile stress 544.44 10 N / m 544.44MN / m 544.44MPa2 9 10−

= ρ =×∴ = = × = =

× ×

IES-12. Ans. (b) Pressure in the main 6 2gh 1000 10 1000 = 10 N / mm 1000 KPa= ρ = × × =

( ) ( )c

6

6c

PdHoop stress2t

10 1Pd 1t m 20 mm2 502 25 10

= σ =

∴ = = = =σ × ×

IES-12(i). Ans. (b)

IES-13. Ans. (a) ( ) [ ] 31 1Hoopstrain = 100 0.3 50 0.425 10200 1000h lE

σ μσ −− = − × = ××

IES-14. Ans. (a) IES-15. Ans. (c) Volumetric stream = 2 × circumferential strain + longitudinal strain (Where E = Modulus of elasticity, μ = Poisson's ratio for the shell material) IES-16. Ans. (c) Remember it. IES-17. Ans. (a) IES-17(i). Ans. (d) IES-18. Ans. (c)

IAS

IAS-1. Ans. (c)

IAS-2. Ans. (c) 2Pr 2 12.5 5 N/mm2 2 2.5t

σ ×= = =×



IAS-3. Ans. (c) Tensile longitudinal stress due to internal fluid pressure (δ 1) t =

2750104

750 10

π

π

⎛ ⎞×× ⎜ ⎟⎝ ⎠× ×

tensile. Compressive longitudinal stress due to external pressure p1 ( δ l)c =2

17504

750 10

P π

π

⎛ ⎞×× ⎜ ⎟⎝ ⎠× ×

compressive. For zero longitudinal stress (δ l) t = (δ l)c.

IAS-4. Ans. (b) For thin cell Pr Pr

2c lt tσ σ= =

IAS-5. Ans. (d) IAS-6. Ans. (d) For thin cylinder, variation of radial strain is zero. So only circumferential and

longitudinal strain has to measurer so only two strain gauges are needed.

IAS-7. Ans. (d) c lc l max

PD PD PDHoop stress( ) and Longitudinalstress( )2t 4t 2 8t

σ σσ σ τ −= = ∴ = =

IAS-8. Ans. (c) Volumetric stream = 2 x circumferential strain + longitudinal strain. IAS-9. Ans. (c) Remember it. IAS-10. Ans. (a)

IAS-11. Ans. (d) ( ) 6PrHoop stress 200 10t aPt

σ = = ×

( ) ( )

( )6

9

PrVolumetric strain ( ) 5 4 5 42 2

200 10 25 4 0.252 200 10 1000

tve

Et Eσμ μ= − = −

×= − × =× ×

IAS-12. Ans. (b)

, 0 and 0

or ,

x y z

x xx y

PA

E E

σ σ σ

σ σε ε μ

= = =

= = −

( ) ( )

( )

and

or 1 2 1 2

. 1 2

xz

xv x y z

v v

EP

E AEPlV V AlE

σε μ

σε ε ε ε μ μ

δ ε ε μ

= −

= + + = − = −

= × = = −

IAS-13. Ans. (b)

3

Volumechange(δV)Volumetricstrain( )Initial volume(V)

1or ( ) 25 10 5 0.255000

v

vV V cm

ε

δ ε

=

= × = × × × =


Conventional Question GATE-1996



Question: A thin cylinder of 100 mm internal diameter and 5 mm thickness is subjected to an internal pressure of 10 MPa and a torque of 2000 Nm. Calculate the magnitudes of the principal stresses.

Answer: Given: d = 100 mm = 0.1 m; t = 5 mm = 0.005 m; D = d + 2t = 0.1 + 2 x 0.005 = 0.11 m p = 10 MPa, 10 x 106N/m2; T= 2000 Nm.

Longitudinal stress, 6

6 2 2l x

pd 10 10 0.1 50 10 N / m 50MN / m4t 4 0.005

σ σ × ×= = = = × =×

Circumferential stress, c ypd2t

σ σ= = =6

210 10 0.1 100MN / m2 0.005× × =×

To find the shear stress, using Torsional equation,

( )( )

( )2

xy4 4 4 4

T ,we haveJ R

2000 0.05 0.005TR T R 24.14MN / mJ D d 0.11 0.1

32 32

τ

τ τ π π

=

× +×= = = = =− −

Principal stresses are:

( )

( )

( )( )

22x y x y

1 2 xy

22

2

21

22

,2 2

50 100 50 100 24.142 2

75 34.75 109.75 and 40.25MN / mMajor principal stress 109.75MN / m ;

minor principal stress 40.25MN / m ;

σ σ σ σσ τ

σ

σ

+ −⎛ ⎞= ± +⎜ ⎟

⎝ ⎠

+ −⎛ ⎞= ± +⎜ ⎟⎝ ⎠

= ± ==

=

Conventional Question IES-2008 Question: A thin cylindrical pressure vessel of inside radius ‘r’ and thickness of metal ‘t’

is subject to an internal fluid pressure p. What are the values of (i) Maximum normal stress? (ii) Maximum shear stress?

Answer: Circumferential (Hoop) stress( )cσ =.p rt

Longitudinal stress( )σ =.

2=

p rt

Therefore (ii) Maximum shear stress, ( τ max) =.r

2 4σ σ−

=c pt

Conventional Question IES-1996 Question: A thin cylindrical vessel of internal diameter d and thickness t is closed at

both ends is subjected to an internal pressure P. How much would be the hoop and longitudinal stress in the material?

Answer: For thin cylinder we know that

Hoop or circumferential stress ( )σ2cPd

t=



And longitudinal stress( )σ =4Pd

t

Therefore σ 2σc = Conventional Question IES-2009 Q. A cylindrical shell has the following dimensions: Length = 3 m Inside diameter = 1 m Thickness of metal = 10 mm Internal pressure = 1.5 MPa Calculate the change in dimensions of the shell and the maximum intensity of

shear stress induced. Take E = 200 GPa and Poisson’s ratio ν = 0.3 [15-Marks] Ans. We can consider this as a thin cylinder.

Hoop stresses,

Longitudinal stresses,

Shear stress =

Hence from the given data

6

81 3

1.5 10 1 0.75 102 10 10−

× ×σ = = ×× ×

66

2 31.5 10 1 37.5 104 10 10

37.5 MPa−

× ×σ = = ×× ×

=

( )

( )

( )

( )

1

1 1 2

6

3 9

6

9

3

3

Hoop strain1 vE

Pd 2 v4tE

1.5 10 1 2 0.34 10 10 200 1037.5 10 2 0.3200 100.31875 10d 0.3187 10

d

−

−

−

ε

ε = σ − σ

= −

× ×= −× × × ×

×= −×

= ×Δ = ×

3 change in diameter,d = 1 × 0.31875 × 10 m

= 0.31875 mm

−

∴

Δ

1pd2t

σ =

2pd4t

σ =

1 22

σ − σ

pd8t

=

75 MPa=



( )

( )

2

2

6

9

5

5

5

4

Logitudinal strain, pd 1 2v4tE

37.5 10 1 2 0.3200 107.5 10l 7.5 10

lor l 7.5 10 3

2.25 10 m 0.225mm

−

−

−

−

ε

∈ = −

×= − ××

= ×Δ = ×

Δ = × ×

= × =

⇒ Change in length = 0.225 mm and maximum shear stress,

Conventional Question IES-1998 Question: A thin cylinder with closed ends has an internal diameter of 50 mm and a

wall thickness of 2.5 mm. It is subjected to an axial pull of 10 kN and a torque of 500 Nm while under an internal pressure of 6 MN/m2

(i) Determine the principal stresses in the tube and the maximum shear stress.

(ii) Represent the stress configuration on a square element taken in the load direction with direction and magnitude indicated; (schematic).

Answer: Given: d = 50 mm = 0.05 m D = d + 2t = 50 + 2 x 2.5 = 55 mm = 0.055 m; Axial pull, P = 10 kN; T= 500 Nm; p = 6MN/m2

(i) Principal stresses ( 1 2,σ ) in the tube and the maximum shear stress ( maxt ):

6 3

x 3 3

6 6 6 2

66

y 3

pd P 6 10 0.05 10 104t dt 4 2.5 10 0.05 2.5 1030 10 25.5 10 55.5 10 N / m

pd 6 10 0.05 60 102t 2 2.5 10

σπ π

σ

− −

−

× × ×= + = +× × × × ×

= × + × = ×× ×= = = ×× ×

Principal stresses are:

( )

( )

( ) ( ) ( )( )

x y x y 21 2 xy

4 44 4 7 4

, 12 2

TUseTorsional equation, iJ R

where J D d 0.055 0.05 2.848 10 m32 32

J polar moment of inertia

σ σ σ σσ τ

τ

π π −

+ −⎛ ⎞ ⎛ ⎞= ± + − − −⎜ ⎟ ⎜ ⎟⎝ ⎠ ⎝ ⎠

= − − −

⎡ ⎤= − = − = ×⎣ ⎦

=

( )Substituting the values in i ,we get

6

3pd 1.5 10 18t 8 10 10

18.75 MPa−

× ×σ = =

× ×=



( )

( )

7

6 27

5000.055 / 22.848 10

500 0.055 / 2or 48.28 10 N / m

2.848 10

τ

τ

−

−

=×

×= = ×

×

Now, substituting the various values in eqn. (i), we have

( )6 6 6 6 26

1 2

612 12

6 6 2 2

2 21 2

55.5 10 60 10 55.5 10 60 10, 48.28 102 2

(55.5 60) 10 4.84 10 2330.96 102

57.75 10 48.33 10 106.08MN / m ,9.42MN / mPrincipal stresses are : 106.08MN / m ; 9.42MN / m

Maximum shea

σ

σ σ

⎛ ⎞ ⎛ ⎞× + × × − ×= ± + ×⎜ ⎟ ⎜ ⎟⎝ ⎠ ⎝ ⎠

+ ×= ± × + ×

= × ± × == =

21 2max

106.08 9.42r stress, 48.33MN / m2 2

σ στ − −= = =

( )ii Stress configuration on a square element :


11. Thick Cylinder

Theory at a Glance (for IES, GATE, PSU) 1. Thick cylinder

iInner dia of the cylinder (d ) 15 or 20wall thickness (t)

<

2. General Expression

3. Difference between the analysis of stresses in thin & thick cylinders

• In thin cylinders, it is assumed that the tangential stress tσ is uniformly distributed over

the cylinder wall thickness.

In thick cylinder, the tangential stress tσ has the highest magnitude at the inner surface of

the cylinder & gradually decreases towards the outer surface.

• The radial stress rσ is neglected in thin cylinders while it is of significant magnitude in case

of thick cylinders.

4. Strain

• Radial strain, .rdudr

∈ =

• Circumferential /Tangential strain tur

∈ =

• Axial strain, tz rz E E E

σσ σμ ⎛ ⎞∈ = − +⎜ ⎟

⎝ ⎠


Chapter-11 Thick Cylinder S K Mondal’s

5. Stress

• Axial stress, 2

2 20

σ =−i i

zi

p rr r

• Radial stress, 2rBAr

σ = −

• Circumferential /Tangential stress, 2tBAr

σ = +

[Note: Radial stress always compressive so its magnitude always –ive. But in some books they

assume that compressive radial stress is positive and they use, 2σ = −rB Ar

]

6. Boundary Conditions

At = ir r , σ = −r ip

At = or r r opσ = −

7. 2 2

2 2

−=−

i i o o

o i

p r p rAr r

and 2 2

2 2( )( )

= −−

i oi o

o i

r rB p pr r

8. Cylinders with internal pressure (pi) i.e. 0op =

• 2

2 20

σ =−i i

zi

p rr r

• 2 2

02 2 2

0

1σ⎡ ⎤

= − −⎢ ⎥− ⎣ ⎦i i

ri

p r rr r r

[ -ive means compressive stress]

• 2 2

02 2 2

0

1σ⎡ ⎤

= + +⎢ ⎥− ⎣ ⎦i i

ti

p r rr r r

(a) At the inner surface of the cylinder

r2 2

t 2 2

2

max 2 2

( )

( )

( )( )

( ) .

i

i

i o i

o i

oi

o i

i r r

ii p

p r riiir r

riv pr r

σ

σ

τ

=

= −

+= +−

=−

(b) At the outer surface of the cylinder

2

i2 2

( ) r = r

( ) 0

2p r( ) =

σ

σ

=

−

o

r

it

o i

i

ii

iiir r



(c) Radial and circumferential stress distribution within the cylinder wall when only

internal pressure acts.

9. Cylinders with External Pressure (po) i.e. 0ip =

• 2 2

r 2 2 2σ⎡ ⎤

= − −⎢ ⎥− ⎣ ⎦o o i

o i

p r rir r r

• 2 2

2 2 2σ⎡ ⎤

= − +⎢ ⎥− ⎣ ⎦o o i

to i

p r rir r r

(a) At the inner surface of the cylinder

(i) r = ir

(ii) r oσ =

(iii) 2

2 2

2σ = −−o o

to i

p rr r

(b) At the outer surface of the cylinder

(i) r = ro

(ii) r opσ = −

(iii) 2 2

2 2

( )σ += −−

o o it

o i

p r rr r

(c) Distribution of radial and circumferential stresses within the cylinder wall when

only external pressure acts

10. Lame's Equation [for Brittle Material, open or closed end] There is a no of equations for the design of thick cylinders. The choice of equation depends upon two parameters.



• Cylinder Material (Whether brittle or ductile)

• Condition of Cylinder ends (open or closed)

When the material of the cylinder is brittle, such as cast iron or cast steel, Lame's Equation is used to

determine the wall thickness. Condition of cylinder ends may open or closed.

It is based on maximum principal stress theory of failure.

There principal stresses at the inner surface of the cylinder are as follows: (i) (ii) & (iii)

2 2

0t 2 2

02

z 2 2

( )

( )( )

( )

σ

σ

σ

= −

+= +−

= +−

r i

i i

i

i i

o i

i p

p r riir r

p riiir r

• tσ σ σ> >z r

• t is the criterion of designσ o

i

σσ

+=−

t i

t i

r pr p

• For o ir r t= +

• t 1σσ

⎡ ⎤+= × −⎢ ⎥−⎢ ⎥⎣ ⎦

t ii

t i

prp

( ' )Lame s Equation

• tσσ = ult

fos

11. Clavarino's Equation [for cylinders with closed end & made of ductile material] When the material of a cylinder is ductile, such as mild steel or alloy steel, maximum strain theory of failure is used (St. Venant's theory) is used.

Three principal stresses at the inner surface of the cylinder are as follows (i) (ii) & (iii)

r2 2

2 2

2

2 2

( )

( )( )( )

( )( )

σ

σ

σ

= −

+= +−

= +−

i

i o it

o i

i iz

o i

i p

p r riir r

p riiir r

• ( )1 σ σ σ⎡ ⎤∈ = − +⎣ ⎦t t r zE

• /σσ∈ = = yld

t

fosE E

• Or yld( ). Where =fosσ

σ σ μ σ σ σ= − +t r z



• σ is the criterion of design

(1 2 )(1 )

σ μσ μ+ −=− +

o i

i i

r pr p

• For ro = ri + t

(1 2 ) 1 (1 )

σ μσ μ

⎡ ⎤+ −= −⎢ ⎥− +⎣ ⎦i

ii

pt rp

( )Clavarion's Equation

12. Birne's Equation [for cylinders with open end & made of ductile material] When the material of a cylinder is ductile, such as mild steel or alloy steel, maximum strain theory

of failure is used (St. Venant's theory) is used.

Three principal stresses at the inner surface of the cylinder are as follows (i) (ii) & (iii)

r2 2

2 2

( )

( )( )( )

( ) 0

σ

σ

σ

= −

+= +−

=

i

i o it

o i

z

i p

p r riir r

iii

• yld where =fosσ

σ σ μσ σ= −t r

• σ is the criterion of design

(1 )(1 )

σ μσ μ+ −=− +

o i

i i

r pr p

• For ro = ri + t

(1 ) 1(1 )

σ μσ μ

⎡ ⎤+ −= × −⎢ ⎥− +⎣ ⎦i

ii

pt rp

(Birnie's Equation)

13. Barlow’s equation: [for high pressure gas pipe brittle or ductile material]

io

t

pt rσ

= [GAIL exam 2004]

Where yt for ductile material

fosσ

σ =

ult for brittle materialfosσ

=

14. Compound Cylinder (A cylinder & A Jacket) • When two cylindrical parts are assembled by shrinking or press-fitting, a contact pressure is

created between the two parts. If the radii of the inner cylinder are a and c and that of the



outer cylinder are (c- δ ) and b, δ being the radial interference the contact pressure is given

by:

( )2 2 2 2

2 2 2

( )2 ( )

b c c aEPc c b aδ ⎡ ⎤− −⎢ ⎥= ⎢ ⎥−⎢ ⎥⎣ ⎦

Where E is the Young's modulus of the material

• The inner diameter of the jacket is slightly smaller than the outer diameter of cylinder

• When the jacket is heated, it expands sufficiently to move over the cylinder

• As the jacket cools, it tends to contract onto the inner cylinder, which induces residual compressive stress.

• There is a shrinkage pressure 'P' between the cylinder and the jacket.

• The pressure 'P' tends to contract the cylinder and expand the jacket

• The shrinkage pressure 'P' can be evaluated from the above equation for a given amount of

interference δ

• The resultant stresses in a compound cylinder are found by supervision losing the 2- stresses

stresses due to shrink fit stresses due to internal pressure

Derivation:

j

δ

δ

δ δ δ

j

c

c

Due to interference let us assume increase in inner diameter

of jacket and decrease in outer diameter of cylinder.

so = + i.e. without sign.

=

=

[ ]

( )( )

j

µ

δ

σ µσ

t2 2 2 2

2 2 2 2

r

Now tangential strain

1 =

σ =circumferential stress

cP p(b +c ) = ( ) +E b -c

σ =-p radialstress

j j

t r

c

cE

b c ib c

⎡ ⎤=∈ ∈ =⎢ ⎥⎣ ⎦

−

⎡ ⎤⎢ ⎥⎢ ⎥

⎡ ⎤ ⎢ ⎥+⎢ ⎥ ⎢ ⎥+ −−−⎢ ⎥ ⎢ ⎥−⎣ ⎦ ⎢ ⎥⎢ ⎥⎢ ⎥⎣ ⎦



[ ] ( )

µ

σδ σ µσ

σ

-

2 2

t 2 2

2 2

2 2

( )1And in similar way =

cP =- ( ) Here -ivesignrepresentscontraction E

c c t r

r

p c ac ac c

Ep

c a iic a

⎡ ⎤+⎢ ⎥=−⎢ ⎥−=∈ − ⎢ ⎥⎢ ⎥

=−⎢ ⎥⎣ ⎦⎡ ⎤+⎢ ⎥ −−−⎢ ⎥−⎣ ⎦

δδ δ δ2 2 2 2 2 2 2

2 2 2 2 2 2 2

Adding ( ) & ( )

2 ( ) ( )( ) or( )( ) 2 ( )j c

i ii

Pc c b a E b c c aPE cb c c a c b a

⎡ ⎤ ⎡ ⎤− − −⎢ ⎥ ⎢ ⎥∴ = + = =⎢ ⎥ ⎢ ⎥− − −⎣ ⎦ ⎣ ⎦

15. Autofrettage Autofrettage is a process of pre-stressing the cylinder before using it in operation.

We know that when the cylinder is subjected to internal pressure, the circumferential stress at the inner surface limits the pressure carrying capacity of the cylinder.

In autofrettage pre-stressing develops a residual compressive stresses at the inner surface. When

the cylinder is actually loaded in operation, the residual compressive stresses at the inner surface begin to decrease, become zero and finally become tensile as the pressure is gradually increased.

Thus autofrettage increases the pressure carrying capacity of the cylinder.

16. Rotating Disc The radial & circumferential (tangential) stresses in a rotating disc of uniform thickness are given

by

( )2 22

2 2 200 23

8ρωσ μ

⎛ ⎞= + + − −⎜ ⎟

⎝ ⎠i

r iR RR R r

r

( )2 22

2 2 200 2

1 33 .8 3

ρω μσ μμ

⎛ ⎞+= + + + −⎜ ⎟+⎝ ⎠i

t iR RR R r

r

Where Ri = Internal radius Ro = External radius

ρ = Density of the disc material

ω = Angular speed

μ = Poisson's ratio.

Or, Hoop’s stress, 2 2 20

μ3 1 μσ . .4 3 μ

ρω⎡ ⎤⎛ ⎞+ −⎛ ⎞= +⎢ ⎥⎜ ⎟⎜ ⎟ +⎝ ⎠ ⎝ ⎠⎣ ⎦

t iR R

Radial stress, 2 2 20

3 .8μσ ρω+⎛ ⎞ ⎡ ⎤= −⎜ ⎟ ⎣ ⎦⎝ ⎠

r iR R





Lame's theory GATE-1. A thick cylinder is subjected to an internal pressure of 60 MPa. If the hoop

stress on the outer surface is 150 MPa, then the hoop stress on the internal surface is: [GATE-1996; IES-2001]

(a) 105 MPa (b) 180 MPa (c) 210 MPa (d) 135 MPa


Thick cylinder IES-1. If a thick cylindrical shell is subjected to internal pressure, then hoop stress,

radial stress and longitudinal stress at a point in the thickness will be: (a) Tensile, compressive and compressive respectively [IES-1999] (b) All compressive (c) All tensile (d) Tensile, compressive and tensile respectively IES-2. Where does the maximum hoop stress in a thick cylinder under external

pressure occur? [IES-2008] (a) At the outer surface (b) At the inner surface (c) At the mid-thickness (d) At the 2/3rd outer radius IES-3. In a thick cylinder pressurized from inside, the hoop stress is maximum at (a) The centre of the wall thickness (b) The outer radius [IES-1998] (c) The inner radius (d) Both the inner and the outer radii IES-5. A thick-walled hollow cylinder having outside and inside radii of 90 mm and 40

mm respectively is subjected to an external pressure of 800 MN/m2. The maximum circumferential stress in the cylinder will occur at a radius of

[IES-1998] (a) 40 mm (b) 60 mm (c) 65 mm (d) 90 mm IES-6. In a thick cylinder, subjected to internal and external pressures, let r1 and r2 be

the internal and external radii respectively. Let u be the radial displacement of a material element at radius r, 2 1r r r≥ ≥ . Identifying the cylinder axis as z axis,

the radial strain component rrε is: [IES-1996] (a) u/r (b) /u θ (c) du/dr (d) du/dθ

Lame's theory IES-7. A thick cylinder is subjected to an internal pressure of 60 MPa. If the hoop

stress on the outer surface is 150 MPa, then the hoop stress on the internal surface is: [GATE-1996; IES-2001]

(a) 105 MPa (b) 180 MPa (c) 210 MPa (d) 135 MPa IES-8. A hollow pressure vessel is subject to internal pressure. [IES-2005] Consider the following statements: 1. Radial stress at inner radius is always zero.



2. Radial stress at outer radius is always zero. 3. The tangential stress is always higher than other stresses. 4. The tangential stress is always lower than other stresses. Which of the statements given above are correct? (a) 1 and 3 (b) 1 and 4 (c) 2 and 3 (d) 2 and 4 IES-9. A thick open ended cylinder as shown in the

figure is made of a material with permissible normal and shear stresses 200 MPa and 100 MPa respectively. The ratio of permissible pressure based on the normal and shear stress is:

[di = 10 cm; do = 20 cm] (a) 9/5 (b) 8/5 (c) 7/5 (d) 4/5

[IES-2002]

Longitudinal and shear stress IES-10. A thick cylinder of internal radius and external radius a and b is subjected to

internal pressure p as well as external pressure p. Which one of the following statements is correct? [IES-2004]

The magnitude of circumferential stress developed is: (a) Maximum at radius r = a (b) Maximum at radius r = b (c) Maximum at radius r = ab (d) Constant IES-11. Consider the following statements: [IES-2007] In a thick walled cylindrical pressure vessel subjected to internal pressure, the

Tangential and radial stresses are: 1. Minimum at outer side 2. Minimum at inner side 3. Maximum at inner side and both reduce to zero at outer wall 4. Maximum at inner wall but the radial stress reduces to zero at outer wall Which of the statements given above is/are correct? (a) 1 and 2 (b) 1 and 3 (c) 1 and 4 (d) 4 only IES-12. Consider the following statements at given point in the case of thick cylinder

subjected to fluid pressure: [IES-2006] 1. Radial stress is compressive 2. Hoop stress is tensile 3. Hoop stress is compressive 4. Longitudinal stress is tensile and it varies along the length 5. Longitudinal stress is tensile and remains constant along the length of the

cylinder Which of the statements given above are correct? (a) Only 1, 2 and 4 (b) Only 3 and 4 (c) Only 1,2 and 5 (d) Only 1,3 and 5 IES-13. A thick cylinder with internal diameter d and outside diameter 2d is subjected

to internal pressure p. Then the maximum hoop stress developed in the cylinder is: [IES-2003]

(a) p (b) 23

p (c) 53

p (d) 2p

Compound or shrunk cylinder IES-14. Autofrettage is a method of: [IES-1996; 2005; 2006] (a) Joining thick cylinders (b) Relieving stresses from thick cylinders (c) Pre-stressing thick cylinders (d) Increasing the life of thick cylinders



IES-15. Match List-I with List-II and select the correct answer using the codes given below the Lists: [IES-2004]

List-I List-II A. Wire winding 1. Hydrostatic stress B. Lame's theory 2. Strengthening of thin cylindrical shell C. Solid sphere subjected to uniform 3. Strengthening of thick cylindrical shell pressure on the surface D. Autofrettage 4. Thick cylinders Coeds: A B C D A B C D (a) 4 2 1 3 (b) 4 2 3 1 (c) 2 4 3 1 (d) 2 4 1 3 IES-16. If the total radial interference between two cylinders forming a compound

cylinder is δ and Young's modulus of the materials of the cylinders is E, then the interface pressure developed at the interface between two cylinders of the same material and same length is: [IES-2005]

(a) Directly proportional of E x δ (b) Inversely proportional of E/ δ (c) Directly proportional of E/ δ (d) Inversely proportional of E / δ IES-17. A compound cylinder with inner radius 5 cm and outer radius 7 cm is made by

shrinking one cylinder on to the other cylinder. The junction radius is 6 cm and the junction pressure is 11 kgf/cm2. The maximum hoop stress developed in the inner cylinder is: [IES-1994]

(a) 36 kgf/cm2 compression (b) 36 kgf/cm2 tension (c) 72 kgf/cm2 compression (d) 72 kgf/cm2 tension.

Thick Spherical Shell IES-18. The hemispherical end of a pressure vessel is fastened to the cylindrical

portion of the pressure vessel with the help of gasket, bolts and lock nuts. The bolts are subjected to: [IES-2003]

(a) Tensile stress (b) Compressive stress (c) Shear stress (d) Bearing stress


Longitudinal and shear stress IAS-1. A solid thick cylinder is subjected to an external hydrostatic pressure p. The

state of stress in the material of the cylinder is represented as: [IAS-1995]



OBJECTIVE ANSWERS

GATE-1. Ans. (c) If internal pressure = pi; External pressure = zero

Circumferential or hoop stress (σc) = 22oi i

2 2 2o i

rp r1

r r r⎡ ⎤

+⎢ ⎥− ⎣ ⎦

At i c op 60MPa, 150MPa and r rσ= = =

222 2 2o oi i i

2 2 2 2 2 2 2io i o o i o i

i

22oi

c 2 2 2o i i

r rr r r 150 5 9150 60 1 120 or or120 4 r 5r r r r r r r

at r r

rr 5 960 1 60 1 210 MPa4 5r r r

σ

⎡ ⎤ ⎛ ⎞∴ = + = = = =⎜ ⎟⎢ ⎥− − − ⎝ ⎠⎣ ⎦∴ =

⎡ ⎤ ⎛ ⎞= + = × × + =⎢ ⎥ ⎜ ⎟− ⎝ ⎠⎣ ⎦

IES-1. Ans. (d) Hoop stress – tensile, radial stress – compressive and longitudinal stress – tensile.

Radial and circumferential stress

distribution within the cylinder wall when only internal pressure acts.

Distribution of radial and circumferential stresses within the cylinder wall when only external pressure acts.

IES-2. Ans. (b) Circumferential or hoop stress = tσ

IES-3. Ans. (c) IES-5. Ans. (a) IES-6. Ans. (c) The strains εr and εθ may be given by

( )θ

θ θ

ε σ σ σ

θ θε σ σ

θ

∂= = − =⎡ ⎤⎣ ⎦∂

+ Δ − Δ= = = −⎡ ⎤⎣ ⎦Δ

1 since 0

1

rr r z

r rr

u vr E

r u r u vr r E

Representation of radial and circumferential strain.

IES-7. Ans. (c) If internal pressure = pi; External pressure = zero



Circumferential or hoop stress (σc) = 22oi i

2 2 2o i

rp r1

r r r⎡ ⎤

+⎢ ⎥− ⎣ ⎦

At i c op 60MPa, 150MPa and r rσ= = =

222 2 2o oi i i

2 2 2 2 2 2 2io i o o i o i

i

22oi

c 2 2 2o i i

r rr r r 150 5 9150 60 1 120 or or120 4 r 5r r r r r r r

at r r

rr 5 960 1 60 1 210 MPa4 5r r r

σ

⎡ ⎤ ⎛ ⎞∴ = + = = = =⎜ ⎟⎢ ⎥− − − ⎝ ⎠⎣ ⎦∴ =

⎡ ⎤ ⎛ ⎞= + = × × + =⎢ ⎥ ⎜ ⎟− ⎝ ⎠⎣ ⎦

IES-8. Ans. (c) IES-9. Ans. (b) IES-10. Ans. (d)

( )

2 2 2 2i i o o

c 2 2 2 2 2o i

2 2i o o i

c 2 2o i

Pr P rB Pa PbA A Pr r r b a

P P r rP B o

r r

σ

σ

− −= + = = = −− −

−∴ = − = =

−

IES-11. Ans. (c) IES-12. Ans. (c) 3. For internal fluid pressure Hoop or circumferential stress is tensile. 4. Longitudinal stress is tensile and remains constant along the length of the cylinder. IES-13. Ans. (c) In thick cylinder, maximum hoop stress

22

2 22 1

22 22 1 2

523

2

hoop

ddr rp p pr r dd

σ

⎛ ⎞+ ⎜ ⎟+ ⎝ ⎠= × = × =− ⎛ ⎞− ⎜ ⎟

⎝ ⎠

IES-14. Ans. (c) IES-15. Ans. (d) IES-16. Ans. (a) ( )

( )( )2 2 22 3 12

2 2 2 23 2 2 1

2D D DPDE D D D D

P E.

δ

α δ

⎡ ⎤−⎢ ⎥=⎢ ⎥⎡ ⎤− −⎣ ⎦⎣ ⎦

∴

Alternatively : if E then Pand if then P so P Eδ α δ

↑ ↑↑ ↑

IES-17. Ans. (c) IES-18. Ans. (a) IAS-1. Ans. (c)



Distribution of radial and circumferential stresses within the cylinder wall when only

external pressure acts.


Conventional Question IES-1997 Question: The pressure within the cylinder of a hydraulic press is 9 MPa. The inside

diameter of the cylinder is 25 mm. Determine the thickness of the cylinder wall, if the permissible tensile stress is 18 N/mm2

Answer: Given: P = 9 MPa = 9 N/mm2, Inside radius, r1 = 12.5 mm; tσ = 18 N/mm2

Thickness of the cylinder:

2 22 1

t 2 22 1

2 222 22

2

2 1

r rUsing the equation; p ,we haver r

r 12.518 9r 12.5

or r 21.65mmThickness of the cylinder r r 21.65 12.5 9.15mm

σ⎡ ⎤+

= ⎢ ⎥−⎣ ⎦⎡ ⎤+

= ⎢ ⎥−⎣ ⎦=

∴ = − = − =

Conventional Question IES-2010 Q. A spherical shell of 150 mm internal diameter has to withstand an internal

pressure of 30 MN/m2. Calculate the thickness of the shell if the allowable stress is 80 MN/m2.

Assume the stress distribution in the shell to follow the law

3 3

2r

b ba and ar rθσ σ= − = + [10 Marks]

Ans. A spherical shell of 150 mm internal diameter internal pressure = 30 MPa. Allowable stress = 80 MN/m2

Assume radial stress =

Circumference stress =

At internal diameter (r)

r 32bar

σ = −

3barθσ = +



r2

2

3

3

n

3

3

33

30N / mm

80N / mm2b30 a ..............(i)

(75)b80 a .................(ii)

(75)Soluing eq (i)&(ii)

110 75 130b a3 3

At outer Radius (R) radial stress should be zero2bo aR

2b 2 110 75R 713130a 33

θ

σ

σ

= −

=

− = −

= +

×= =

= −

× ×= = =×

942.3077

R 89.376mmThere fore thickness of cylinder = (R r)

89.376 75 14.376mm

=−

= − =

Conventional Question IES-1993 Question: A thick spherical vessel of inner 'radius 150 mm is subjected to an internal

pressure of 80 MPa. Calculate its wall thickness based upon the (i) Maximum principal stress theory, and (ii) Total strain energy theory. Poisson's ratio = 0.30, yield strength = 300 MPa Answer: Given:

( ) 6 21 r

6 2

1r 150mm; p 80MPa 80 10 N / m ; 0.30;m

300MPa 300 10 N / mWall thickness t :

σ μ

σ

= = = × = =

= = ×

( )2

2r 2

1

26 6

2

i Maximum principal stress theory :

rK 1We know that, Where KrK 1

K 1or 80 10 300 10K 1

σ σ⎛ ⎞⎛ ⎞+ ≤ =⎜ ⎟⎜ ⎟−⎝ ⎠ ⎝ ⎠

⎛ ⎞+× ≤ ×⎜ ⎟−⎝ ⎠

22 1

1

2 1

or K 1.314or K 1.314

ri.e. 1.314 or r r 1.314 150 1.314 197.1mmr

Metal thickness, t r r 197.1 150 47.1 mm

≥=

= = × = × =

∴ = − = − =

(ii) Total strain energy theory:

2 2 21 2 1 2 yUse σ σ μσ σ σ+ − ≤



( ) ( )( )

( ) ( ) ( ) ( )( )

( ) ( )

2 4r2

22

26 426

22

22 2 2 4

22

1

2 1

2 K 1 1

K 1

2 80 10 K 1 03 1 0.3300 10

K 1

or 300 K 1 2 80 1.3K 0.7

gives K 1.86 or 0.59It is clear thatK 1

K 1.364ror 1.364 or r 150 1.364 204.6 mmrt r r 204.6 150 54.6 mm

σ μ μσ

⎡ ⎤+ + −⎣ ⎦≥−

⎡ ⎤× × + + −⎣ ⎦∴ × ≥−

− = × +

=>

∴ =

= = × =

∴ = − = − =

Conventional Question ESE-2002 Question: What is the difference in the analysis of think tubes compared to that for thin

tubes? State the basic equations describing stress distribution in a thick tube.

Answer: The difference in the analysis of stresses in thin and thick cylinder: (i) In thin cylinder, it is assumed that the tangential stress is uniformly distributed

over the cylinder wall thickness. In thick cylinder, the tangential stress has highest magnitude at the inner surface of the cylinder and gradually decreases towards the outer surface.

(ii) The radial stress is neglected in thin cylinders, while it is of significant magnitude in case of thick cylinders.

Basic equation for describing stress distribution in thick tube is Lame's equation.

2 2 and r tB BA Ar r

σ σ= − = +

Conventional Question ESE-2006 Question: What is auto frettage? How does it help in increasing the pressure carrying capacity of a thick

cylinder? Answer: Autofrettage is a process of pre-stressing the cylinder before using it in operation.

We know that when the cylinder is subjected to internal pressure, the circumferential stress at the inner surface limits the pressure carrying capacity of the cylinder.

In autofrettage pre-stressing develops a residual compressive stresses at the inner surface. When the cylinder is actually loaded in operation, the residual compressive stresses at the inner surface begin to decrease, become zero and finally become tensile as the pressure is gradually increased. Thus autofrettage increases the pressure carrying capacity of the cylinder.

Conventional Question ESE-2001 Question: When two cylindrical parts are assembled by shrinking or press-fitting, a

contact pressure is created between the two parts. If the radii of the inner cylinder are a and c and that of the outer cylinder are (c- δ ) and b, δ being the radial interference the contact pressure is given by:

( )2 2 2 2

2 2 2

( )2 ( )

b c c aEPc c b aδ ⎡ ⎤− −⎢ ⎥= ⎢ ⎥−⎢ ⎥⎣ ⎦



Where E is the Young's modulus of the material, Can you outline the steps involved in developing this important design equation?

Answer:

j

δ

δ

δ δ δ

j

c

c

Due to interference let us assume increase in inner diameter

of jacket and decrease in outer diameter of cylinder.

so = + i.e. without sign.

=

=

[ ]

( )( )

j

µ

δ

σ µσ

t

2 2 2 2

2 2 2 2

r

Now tangential strain

1 =

σ =circumferential stress

cP p(b +c ) = ( ) +E b -c

σ =-p radialstress

j j

t r

c

cE

b c ib c

⎡ ⎤=∈ ∈ =⎢ ⎥⎣ ⎦

−

⎡ ⎤⎢ ⎥⎢ ⎥

⎡ ⎤ ⎢ ⎥+⎢ ⎥ ⎢ ⎥+ −−−⎢ ⎥ ⎢ ⎥−⎣ ⎦ ⎢ ⎥⎢ ⎥⎢ ⎥⎣ ⎦

[ ] ( )

µ

δ

σσ µσ

σ

-

2 2

t 2 2

2 2

2 2

And in similar way

( )1 =

cP =- ( ) Here -ivesignrepresentscontraction E

c c

t r

r

c

p c ac ac

Ep

c a iic a

=∈

⎡ ⎤+⎢ ⎥=−⎢ ⎥−− ⎢ ⎥⎢ ⎥

=−⎢ ⎥⎣ ⎦⎡ ⎤+⎢ ⎥ −−−⎢ ⎥−⎣ ⎦



δ δ δ

δ

2 2 2

2 2 2 2

2 2 2 2

2 2 2

Adding ( ) & ( )

2 ( )( )( )

( )( ) Proved.2 ( )

j c

i ii

Pc c b aE b c c a

E b c c aor Pc c b a

⎡ ⎤−⎢ ⎥∴ = + = ⎢ ⎥− −⎣ ⎦⎡ ⎤− −⎢ ⎥= ⎢ ⎥−⎣ ⎦

Conventional Question ESE-2003 Question: A steel rod of diameter 50 mm is forced into a bronze casing of outside

diameter 90 mm, producing a tensile hoop stress of 30 MPa at the outside diameter of the casing.

Find (i) The radial pressure between the rod and the casing (ii) The shrinkage allowance and (iii) The rise in temperature which would just eliminate the force fit. Assume the following material properties: Es = 2×105 MPa, 0.25 Sμ = , 51.2 10 /o

s Cα −= ×

Eb = 1×105 MPa , 50.3, 1.9 10 /ob b Cμ α −= = ×

Answer:

There is a shrinkage pressure P between the steel rod and the bronze casing. The

pressure P tends to contract the steel rod and expand the bronze casing. (i) Consider Bronze casing, According to Lames theory

σ

2 2i 0 0

2 2 20

2 2i 0 0

2 20

P Where A =

(P ) and B =

it

i

i

i

r P rB Ar r r

P r rr r

−= +

−

−−

0

2 22 20i

2 2 2 2 2 20 0 0

, P 0 and

PrPr 2PrA= , B=r

i

i i

i i i

P P

rr r r r r

= =

=− − −

2 2 2i i i

2 2 2 2 2 2 20 0 0

22 2 20 0

2 2

Pr Pr 2Pr30 r r r

30(r ) 90, P= 15 1 15 1 MPa=33.6MPa502

Therefore the radial pressure between the rod and the casing is P=

o i i i

i

i i

B Ar r r r

r ror

r r

∴ = + = + =− − −

⎡ ⎤⎡ ⎤ ⎛ ⎞− ⎢ ⎥⎟⎜⎢ ⎥= − = −⎟⎜⎢ ⎥⎟⎢ ⎥ ⎜⎝ ⎠⎢ ⎥⎣ ⎦ ⎣ ⎦ 33.6 MPa.

(ii) The shrinkage allowance: Let δ j = increase in inert diameter of bronze casing δ C= decrease in outer diameter of steel rod 1st consider bronze casing:



( )

σt 2

2

2 2 220 0 1

2 2 2 2 22 20 0 0

Tangential stress at the inner surface( )

90 1Pr ( )Pr 50 = 33.6 = 63.6MPa

r 90 150

ji

i

i i i

B Ar

P r rr r r r r

= +

⎡ ⎤⎛ ⎞⎢ ⎥⎟⎜ +⎟⎜⎢ ⎥⎟⎜⎝ ⎠+ ⎢ ⎥+ = = ×⎢ ⎥− − ⎛ ⎞− ⎢ ⎥⎟⎜ −⎟⎜⎢ ⎥⎟⎜⎝ ⎠⎢ ⎥⎣ ⎦

σ

σrand radial stress( ) 33.6

longitudial stress( ) 0j

j

P MPa=− =−

=

( )σ µ σ

δ

-45

4

1Therefore tangential strain ( ) ( )

1 = [63.6 0.3 33.6] =7.368×101×10

( ) 7.368 10 0.050 0.03684mm

t j t r jj

j t j i

E

d

ε

ε −

⎡ ⎤= −⎢ ⎥⎣ ⎦

+ ×

∴ = × = × × =

2nd Consider steel rod:

( )

[ ]

σσ

δ σ µ σ

µ

t

r

5

j c

Circumferential stress ( ) radial stress ( )

1( ) ( )

33.6 0.050(1 ) 1 0.25 0.00588mm [reduction]2 10

Total shrinkage = δ + δ =0.04mm[it is diametral] = 0.

s

s

c t s i t r s iSs

i

s

Pand P

d dE

PdE

=−

=−

⎡ ⎤∴ = ∈ × = − ×⎢ ⎥⎣ ⎦

×=− − =− − =−

×

02mm [radial]

(iii) Let us temperature rise is ( tΔ )

As b sα α> due to same temperature rise steel not will expand less than bronze casing. When their difference of expansion will be equal to the shrinkage then force fit will eliminate.

5 5

0.042720.04272 0.04272 122

50 1.9 10 1.2 10

i b i s

o

i b s

d t d t

or t Cd

α α

α α − −

× ×Δ − × ×Δ =

= = =⎡ ⎤ ⎡ ⎤− × × − ×⎢ ⎥ ⎢ ⎥⎣ ⎦ ⎣ ⎦

Conventional Question AMIE-1998 Question: A thick walled closed-end cylinder is made of an AI-alloy (E = 72 GPa,

1 0.33),m

= has inside diameter of 200 mm and outside diameter of 800 mm.

The cylinder is subjected to internal fluid pressure of 150 MPa. Determine the principal stresses and maximum shear stress at a point on the inside surface of the cylinder. Also determine the increase in inside diameter due to fluid pressure.

Answer: Given: 21 2

200 800r 100mm 0.1m;r 400mm 0.4;p 150MPa 150MN / m ;2 2

= = = = = = = =

9 2 1E 72GPa 72 10 N / m ; 0.33m

μ= = × = =

Principal stress and maximum shear stress: Using the condition in Lame’s equation:



r 2

22

2

b ar

At r 0.1m, p 150MN / mr 0.4m, 0

σ

σσ

= −

= = + == =

Substituting the values in the above equation we have

( )( )

( )( )

( ) ( )

2

2

b150 a i0.1b0 a ii

0.4

From i and ii ,wegeta 10 and b 1.6

= − − − − −

= − − − − −

= =

( )

( ) ( ) ( )

( ) ( ) ( )

c 2

2c 1 2max

2c 2 2min

2 2

The circumferential or hoop stress by Lame's equation,is given byb ar

1.6,at r r 0.1m 10 170MN / m tensile , and0.1

1.6,at r r 0.4m 10 20MN / m tensile .0.4

Pr incipal stresses are 170 MN / m and 20MN / m

Maxi

σ

σ

σ

= +

∴ = = = + =

= = = + =

∴

( ) ( )c c 2max minmax

170 20mum shear stress, 75MN / m2 2

σ στ

− −= = =

( ) ( )

( ) ( )

δ

σ×

= = =− −

122

21l 2 22 2

2 1

Increase in inside diameter, d :

150 0.1prWe know,longitudinal or axial stress, 10MN / mr r 0.4 0.1

( )

( ) ( )6 61 c r l 9

Circumferential or hoop strain at the inner radius,is given by :1 1 170 10 0.33 150 10 10 0.003E 72 10

σ μ σ σ ⎡ ⎤⎡ ⎤∈ = + − = × + − × =⎣ ⎦ ⎣ ⎦×

11

1

dAlso,dδ∈ =

1dor 0.0030.1δ

=

1d 0.003 0.1 0.003m or 0.3 mmδ = × =


12. Spring

Theory at a Glance (for IES, GATE, PSU) 1. A spring is a mechanical device which is used for the efficient storage

and release of energy.

2. Helical spring – stress equation Let us a close-coiled helical spring has coil diameter D, wire diameter d and number of turn n. The

spring material has a shearing modulus G. The spring index,DCd

= . If a force ‘P’ is exerted in both

ends as shown.

The work done by the axial

force 'P' is converted into strain energy and stored in

the spring.

( )( )

U= average torque

× angular displacementT = ×θ2

TLFrom the figure we get, θ =GJ

PDTorque (T)=2

4

2 3

4

length of wire (L)=πDnπdPolar moment of Inertia(J)=32

4P D nTherefore U= Gd

According to Castigliano's theorem, the displacement corresponding to force P is obtained by partially differentiating strain energy with respect to that force.

2 3 3

4 4

4 8UTherefore = p D n PD nP P Gd Gd

δ⎡ ⎤∂∂ ⎢ ⎥= =⎢ ⎥∂ ∂ ⎣ ⎦

Axial deflection3

4

8 = PD nGd

δ

Spring stiffness or spring constant ( )4

3

Pk =8GdD nδ

=


Chapter-12 Spring S K Mondal’s

The torsional shear stress in the bar, ( )1 3 3 3

16 / 216 8PDT PDd d d

τπ π π

= = =

The direct shear stress in the bar, 2 2 32

4 8 0.5

4

P P PD dDd dd

τπ ππ

⎛ ⎞= = = ⎜ ⎟⎛ ⎞ ⎝ ⎠⎜ ⎟⎝ ⎠

Therefore the total shear stress, 1 2 3 3

8 0.5 81 sPD d PDK

Dd dτ τ τ

π π⎛ ⎞= + = + =⎜ ⎟⎝ ⎠

3

8s

PDKd

τπ

=

Where 0.51s

dKD

= + is correction factor for direct shear stress.

3. Wahl’s stress correction factor

3

8PDKd

τπ

=

Where 4 1 0.6154 4

CKC C

−⎛ ⎞= +⎜ ⎟−⎝ ⎠is known as Wahl’s stress correction factor

Here K = KsKc; Where sK is correction factor for direct shear stress and Kc is correction

factor for stress concentration due to curvature.

Note: When the spring is subjected to a static force, the effect of stress concentration is neglected

due to localized yielding. So we will use, 3

8s

PDKd

τπ

=

4. Equivalent stiffness (keq) Spring in series 1 2(δ δ δ )e = + Spring in Parallel 1 2(δ δ = δ )=e

eq 1 2

1 1 1 K K K

= + or 1 2

1 2

=+eq

K KKK K

eq 1 2 K = +K K

Shaft in series ( 1 2θ θ θ= + ) Shaft in Parallel ( 1 2θ θ θ= =eq )



eq 1 2

1 1 1 K K K

= + or 1 2

1 2

=+eq

K KKK K

eq 1 2 K = +K K

5. Important note

• If a spring is cut into ‘n’ equal lengths then spring constant of each new spring = nk • When a closed coiled spring is subjected to an axial couple M then the rotation,

4

64φ = cMDnEd

6. Laminated Leaf or Carriage Springs

• Central deflection, 3

3

3δ8

= PLEnbt

• Maximum bending stress, max 2

3σ2

= PLnbt

Where P = load on spring b = width of each plate n = no of plates L= total length between 2 points t =thickness of one plate.

7. Belleville Springs

32 2

0

4 δ δLoad, ( δ)(1 μ ) 2

⎡ ⎤⎛ ⎞= − − +⎜ ⎟⎢ ⎥− ⎝ ⎠⎣ ⎦f

EP h h t tk D

Where, E = Modulus of elasticity δ= Linear deflection μ =Poisson’s Ratio kf =factor for Belleville spring Do = outside diamerer h = Deflection required to flatten Belleville spring t = thickness

Note: • Total stiffness of the springs kror = stiffness per spring × No of springs • In a leaf spring ratio of stress between full length and graduated leaves = 1.5 • Conical spring- For application requiring variable stiffness • Belleville Springs -For application requiring high capacity springs into small space

Do

t

P

ho





Helical spring GATE-1. If the wire diameter of a closed coil helical spring subjected to compressive

load is increased from 1 cm to 2 cm, other parameters remaining same, then deflection will decrease by a factor of: [GATE-2002]

(a) 16 (b) 8 (c) 4 (d) 2 GATE-2. A compression spring is made of music wire of 2 mm diameter having a shear

strength and shear modulus of 800 MPa and 80 GPa respectively. The mean coil diameter is 20 mm, free length is 40 mm and the number of active coils is 10. If the mean coil diameter is reduced to 10 mm, the stiffness of the spring is approximately [GATE-2008]

(a) Decreased by 8 times (b) Decreased by 2 times (c) Increased by 2 times (d) Increased by 8 times GATE-3. Two helical tensile springs of the same material and also having identical mean

coil diameter and weight, have wire diameters d and d/2. The ratio of their stiffness is: [GATE-2001]

(a) 1 (b) 4 (c) 64 (d) 128 GATE-4. A uniform stiff rod of length 300 mm

and having a weight of 300 N is pivoted at one end and connected to a spring at the other end. For keeping the rod vertical in a stable position the minimum value of spring constant K needed is:

(a) 300 N/m (b) 400N/m (c) 500N/m (d) 1000 N/m

[GATE-2004]

GATE-5. A weighing machine consists of a 2 kg pan resting on spring. In this condition,

with the pan resting on the spring, the length of the spring is 200 mm. When a mass of 20 kg is placed on the pan, the length of the spring becomes 100 mm. For the spring, the un-deformed length lo and the spring constant k (stiffness) are: [GATE-2005]

(a) lo = 220 mm, k = 1862 N/m (b) lo = 210 mm, k = 1960 N/m (c) lo = 200 mm, k = 1960 N/m (d) lo = 200 mm, k = 2156 N/m

Springs in Series GATE-6. The deflection of a spring with 20 active turns under a load of 1000 N is 10 mm.

The spring is made into two pieces each of 10 active coils and placed in parallel under the same load. The deflection of this system is: [GATE-1995]

(a) 20 mm (b) 10 mm (c) 5 mm (d) 2.5 mm




Helical spring IES-1. A helical coil spring with wire diameter ’d’ and coil diameter 'D' is subjected to

external load. A constant ratio of d and D has to be maintained, such that the extension of spring is independent of d and D. What is this ratio? [IES-2008]

4/3 4/3

3 4 3 43 3

D d(a)D / d (b)d / D (c) (d)d D

IES-1(i). If both the mean coil diameter and wire diameter of a helical compression or

tension spring be doubled, then the deflection of the spring close coiled under same applied load will [IES-2012] (a) be doubled (b) be halved (c) increase four times (d) get reduced to one – fourth

IES-2. Assertion (A): Concentric cylindrical helical springs are used to have greater

spring force in a limited space. [IES-2006] Reason (R): Concentric helical springs are wound in opposite directions to

prevent locking of coils under heavy dynamic loading. (a) Both A and R are individually true and R is the correct explanation of A (b) Both A and R are individually true but R is NOT the correct explanation of A (c) A is true but R is false (d) A is false but R is true IES-3. Assertion (A): Two concentric helical springs used to provide greater spring

force are wound in opposite directions. [IES-1995; IAS-2004] Reason (R): The winding in opposite directions in the case of helical springs

prevents buckling. (a) Both A and R are individually true and R is the correct explanation of A (b) Both A and R are individually true but R is NOT the correct explanation of A (c) A is true but R is false (d) A is false but R is true IES-4. Which one of the following statements is correct? [IES-1996; 2007; IAS-1997] If a helical spring is halved in length, its spring stiffness (a) Remains same (b) Halves (c) Doubles (d) Triples IES-4(i). A closely coiled spring of 20 cm mean diameter is having 25 coils of 2 cm

diameter. Modulus of rigidity of the material is 210 N/ cm .7 Stiffness of spring is: (a) 50 N/cm (b) 250 N/cm (c) 100 N/cm (d) 500 N/cm [IES-2013] IES-5. A body having weight of 1000 N is dropped from a height of 10 cm over a close-

coiled helical spring of stiffness 200 N/cm. The resulting deflection of spring is nearly [IES-2001]

(a) 5 cm (b) 16 cm (c) 35 cm (d) 100 cm IES-6. A close-coiled helical spring is made of 5 mm diameter wire coiled to 50 mm

mean diameter. Maximum shear stress in the spring under the action of an axial force is 20 N/mm2. The maximum shear stress in a spring made of 3 mm diameter wire coiled to 30 mm mean diameter, under the action of the same force will be nearly [IES-2001]

(a) 20 N/mm2 (b) 33.3 N/mm2 (c) 55.6 N/mm2 (d) 92.6 N/mm2 IES-7. A closely-coiled helical spring is acted upon by an axial force. The maximum

shear stress developed in the spring is τ . Half of the length of the spring is cut off and the remaining spring is acted upon by the same axial force. The maximum shear stress in the spring the new condition will be: [IES-1995]



(a) ½ τ (b) τ (c) 2 τ (d) 4 τ IES-8. The maximum shear stress occurs on the outermost fibers of a circular shaft

under torsion. In a close coiled helical spring, the maximum shear stress occurs on the [IES-1999]

(a) Outermost fibres (b) Fibres at mean diameter (c) Innermost fibres (d) End coils IES-9. A helical spring has N turns of coil of diameter D, and a second spring, made of

same wire diameter and of same material, has N/2 turns of coil of diameter 2D. If the stiffness of the first spring is k, then the stiffness of the second spring will be: [IES-1999]

(a) k/4 (b) k/2 (c) 2k (d) 4k IES-10. A closed-coil helical spring is subjected to a torque about its axis. The spring

wire would experience a [IES-1996; 1998] (a) Bending stress (b) Direct tensile stress of uniform intensity at its cross-section (c) Direct shear stress (d) Torsional shearing stress IES-11. Given that: [IES-1996] d = diameter of spring, R = mean radius of coils, n = number of coils and G =

modulus of rigidity, the stiffness of the close-coiled helical spring subject to an axial load W is equal to

(a) 4

364Gd

R n (b)

3

364Gd

R n (c)

4

332Gd

R n (d)

4

264Gd

R n

IES-12. A closely coiled helical spring of 20 cm mean diameter is having 25 coils of 2 cm

diameter rod. The modulus of rigidity of the material if 107 N/cm2. What is the stiffness for the spring in N/cm? [IES-2004]

(a) 50 (b) 100 (c) 250 (d) 500 IES-13. Which one of the following expresses the stress factor K used for design of

closed coiled helical spring? [IES-2008]

4C 4 4C 1 0.615 4C 4 0.615 4C 1(a) (b) (c) (d)4C 1 4C 4 C 4C 1 C 4C 4

− − − −+ +− − − −

Where C = spring index IES-14. In the calculation of induced shear stress in helical springs, the Wahl's

correction factor is used to take care of [IES-1995; 1997] (a) Combined effect of transverse shear stress and bending stresses in the wire. (b) Combined effect of bending stress and curvature of the wire. (c) Combined effect of transverse shear stress and curvature of the wire. (d) Combined effect of torsional shear stress and transverse shear stress in the wire. IES-15. While calculating the stress induced in a closed coil helical spring, Wahl's

factor must be considered to account for [IES-2002] (a) The curvature and stress concentration effect (b) Shock loading (c) Poor service conditions (d) Fatigue loading IES-16. Cracks in helical springs used in Railway carriages usually start on the inner

side of the coil because of the fact that [IES-1994] (a) It is subjected to the higher stress than the outer side. (b) It is subjected to a higher cyclic loading than the outer side. (c) It is more stretched than the outer side during the manufacturing process. (d) It has a lower curvature than the outer side. IES-17. Two helical springs of the same material and of equal circular cross-section

and length and number of turns, but having radii 20 mm and 40 mm, kept concentrically (smaller radius spring within the larger radius spring), are



compressed between two parallel planes with a load P. The inner spring will carry a load equal to [IES-1994]

(a) P/2 (b) 2P/3 (c) P/9 (d) 8P/9 IES-18. A length of 10 mm diameter steel wire is coiled to a close coiled helical spring

having 8 coils of 75 mm mean diameter, and the spring has a stiffness K. If the same length of wire is coiled to 10 coils of 60 mm mean diameter, then the spring stiffness will be: [IES-1993]

(a) K (b) 1.25 K (c) 1.56 K (d) 1.95 K IES-18a. Two equal lengths of steel wires of the same diameter are made into two

springs S1 and S2 of mean diameters 75 mm and 60 mm respectively. The stiffness ratio of S1 to S2 is [IES-2011]

2 3 2 360 60 75 75( ) ( ) ( ) ( )75 75 60 60

a b c d⎛ ⎞ ⎛ ⎞ ⎛ ⎞ ⎛ ⎞⎜ ⎟ ⎜ ⎟ ⎜ ⎟ ⎜ ⎟⎝ ⎠ ⎝ ⎠ ⎝ ⎠ ⎝ ⎠

IES-19. A spring with 25 active coils cannot be accommodated within a given space.

Hence 5 coils of the spring are cut. What is the stiffness of the new spring? (a) Same as the original spring (b) 1.25 times the original spring [IES-2004, 2012] (c) 0.8 times the original spring (d) 0.5 times the original spring IES-20. Wire diameter, mean coil diameter and number of turns of a closely-coiled steel

spring are d, D and N respectively and stiffness of the spring is K. A second spring is made of same steel but with wire diameter, mean coil diameter and number of turns 2d, 2D and 2N respectively. The stiffness of the new spring is:

[IES-1998; 2001] (a) K (b) 2K (c) 4K (d) 8K IES-21. When two springs of equal lengths are arranged to form cluster springs which

of the following statements are the: [IES-1992] 1. Angle of twist in both the springs will be equal 2. Deflection of both the springs will be equal 3. Load taken by each spring will be half the total load 4. Shear stress in each spring will be equal (a) 1 and 2 only (b) 2 and 3 only (c) 3 and 4 only (d) 1, 2 and 4 only IES-22. Consider the following statements: [IES-2009] When two springs of equal lengths are arranged to form a cluster spring 1. Angle of twist in both the springs will be equal 2. Deflection of both the springs will be equal 3. Load taken by each spring will be half the total load 4. Shear stress in each spring will be equal Which of the above statements is/are correct? (a) 1 and 2 (b) 3 and 4 (c)2 only (d) 4 only IES-22(i). The compliance of the spring is the: [IES-2013] (a) Reciprocal of the spring constant (b) Deflection of the spring under compressive load (c) Force required to produce a unit elongation of the spring (d) Square of the stiffness of the spring IES-22(ii). A bumper consisting of two helical springs of circular section brings to rest a

railway wagon of mass 1500 kg and moving at 1 m/s. While doing so, the springs are compressed by 150 mm. Then, the maximum force on each spring (assuming gradually increasing load) is: [IES-2013]

(a) 2500 N (b) 5000 N (c) 7500 N (d) 3000 N



Close-coiled helical spring with axial load IES-23. Under axial load, each section of a close-coiled helical spring is subjected to (a) Tensile stress and shear stress due to load [IES-2003] (b) Compressive stress and shear stress due to torque (c) Tensile stress and shear stress due to torque (d) Torsional and direct shear stresses IES-24. When a weight of 100 N falls on a spring of stiffness 1 kN/m from a height of 2

m, the deflection caused in the first fall is: [IES-2000] (a) Equal to 0.1 m (b) Between 0.1 and 0.2 m (c) Equal to 0.2 m (d) More than 0.2 m

Subjected to 'Axial twist' IES-25. A closed coil helical spring of mean coil diameter 'D' and made from a wire of

diameter 'd' is subjected to a torque 'T' about the axis of the spring. What is the maximum stress developed in the spring wire? [IES-2008]

π π π π3 3 3 3

8T 16T 32T 64T(a) (b) (c) (d)d d d d

Springs in Series IES-26. When a helical compression spring is cut into two equal halves, the stiffness of

each of the result in springs will be: [IES-2002; IAS-2002] (a) Unaltered (b) Double (c) One-half (d) One-fourth IES-27. If a compression coil spring is cut into two equal parts and the parts are then

used in parallel, the ratio of the spring rate to its initial value will be: [IES-1999] (a) 1 (b) 2 (c) 4 (d) Indeterminable for want of sufficient data

Springs in Parallel IES-28. The equivalent spring stiffness for the

system shown in the given figure (S is the spring stiffness of each of the three springs) is:

(a) S/2 (b) S/3 (c) 2S/3 (d) S

[IES-1997; IAS-2001]

IES-29. Two coiled springs, each having stiffness K, are placed in parallel. The stiffness of the combination will be: [IES-2000]

( ) ( ) ( ) ( )a 4 b 2 c d 2 4K KK K

IES-30. A mass is suspended at the bottom of two springs in series having stiffness 10

N/mm and 5 N/mm. The equivalent spring stiffness of the two springs is nearly [IES-2000]

(a) 0.3 N/mm (b) 3.3 N/mm (c) 5 N/mm (d) 15 N/mm



IES-31. Figure given above shows a spring-mass system where the mass m is fixed in between two springs of stiffness S1 and S2. What is the equivalent spring stiffness?

(a) S1- S2 (b) S1+ S2

(c) (S1+ S2)/ S1 S2 (d) (S1- S2)/ S1 S2

[IES-2005]

IES-32. Two identical springs labelled as 1 and 2 are arranged in series and subjected to force F as shown in the given figure.

Assume that each spring constant is K. The strain energy stored in spring 1 is: [IES-2001]

(a) 2

2FK

(b) 2

4FK

(c) 2

8FK

(d) 2

16F

K

IES-33. What is the equivalent stiffness (i.e. spring

constant) of the system shown in the given figure?

(a) 24 N/mm (b) 16 N/mm (c) 4 N/mm (d) 5.3 N/mm

[IES-1997]


Helical spring IAS-1. Assertion (A): Concentric cylindrical helical springs which are used to have

greater spring force in a limited space is wound in opposite directions. Reason (R): Winding in opposite directions prevents locking of the two coils in

case of misalignment or buckling. [IAS-1996] (a) Both A and R are individually true and R is the correct explanation of A (b) Both A and R are individually true but R is NOT the correct explanation of A (c) A is true but R is false (d) A is false but R is true IAS-2. An open-coiled helical spring of mean diameter D, number of coils N and wire

diameter d is subjected to an axial force' P. The wire of the spring is subject to: [IAS-1995]

(a) direct shear only (b) combined shear and bending only (c) combined shear, bending and twisting (d) combined shear and twisting only



IAS-3. Assertion (A): Two concentric helical springs used to provide greater spring

force are wound in opposite directions. [IES-1995; IAS-2004] Reason (R): The winding in opposite directions in the case of helical springs

prevents buckling. (a) Both A and R are individually true and R is the correct explanation of A (b) Both A and R are individually true but R is NOT the correct explanation of A (c) A is true but R is false (d) A is false but R is true IAS-4. Which one of the following statements is correct? [IES-1996; 2007; IAS-1997] If a helical spring is halved in length, its spring stiffness (a) Remains same (b) Halves (c) Doubles (d) Triples IAS-5. A closed coil helical spring has 15 coils. If five coils of this spring are removed

by cutting, the stiffness of the modified spring will: [IAS-2004] (a) Increase to 2.5 times (b) Increase to 1.5 times (c) Reduce to 0.66 times (d) Remain unaffected IAS-6. A close-coiled helical spring has wire diameter 10 mm and spring index 5. If the

spring contains 10 turns, then the length of the spring wire would be: [IAS-2000] (a) 100 mm (b) 157 mm (c) 500 mm (d) 1570 mm IAS-7. Consider the following types of stresses: [IAS-1996] 1. torsional shear 2. Transverse direct shear 3. Bending stress The stresses, that are produced in the wire of a close-coiled helical spring

subjected to an axial load, would include (a) 1 and 3 (b) 1 and 2 (c) 2 and 3 (d) 1, 2 and 3 IAS-8. Two close-coiled springs are subjected to the same axial force. If the second

spring has four times the coil diameter, double the wire diameter and double the number of coils of the first spring, then the ratio of deflection of the second spring to that of the first will be: [IAS-1998]

(a) 8 (b) 2 (c) 12

(d) 1/16

IAS-9. A block of weight 2 N falls from a height of 1m on the top of a spring· If the spring gets compressed by 0.1 m to bring the weight momentarily to rest, then the spring constant would be: [IAS-2000]

(a) 50 N/m (b) 100 N/m (c) 200N/m (d) 400N/m IAS-10. The springs of a chest expander are 60 cm long when unstretched. Their

stiffness is 10 N/mm. The work done in stretching them to 100 cm is: [IAS-1996] (a) 600 Nm (b) 800 Nm (c) 1000 Nm (d) 1600 Nm IAS-11. A spring of stiffness 'k' is extended from a displacement x1 to a displacement x2

the work done by the spring is: [IAS-1999]

(a) 2 21 2

1 12 2

−k x k x (b) 21 2

1 ( )2

−k x x (c) 21 2

1 ( )2

+k x x (d) 2

1 2

2x xk +⎛ ⎞

⎜ ⎟⎝ ⎠

IAS-12. A spring of stiffness 1000 N/m is stretched initially by 10 cm from the

undeformed position. The work required to stretch it by another 10 cm is: [IAS-1995]

(a) 5 Nm (b) 7 Nm (c) 10 Nm (d) 15 Nm.

Springs in Series IAS-13. When a helical compression spring is cut into two equal halves, the stiffness of

each of the result in springs will be: [IES-2002; IAS-2002] (a) Unaltered (b) Double (c) One-half (d) One-fourth



IAS-14. The length of the chest-expander spring when it is un-stretched, is 0.6 m and its

stiffness is 10 N/mm. The work done in stretching it to 1m will be: [IAS-2001] (a) 800 J (b) 1600 J (c) 3200 J (d) 6400 J

Springs in Parallel IAS-15. The equivalent spring stiffness for the

system shown in the given figure (S is the spring stiffness of each of the three springs) is:

(a) S/2 (b) S/3 (c) 2S/3 (d) S

[IES-1997; IAS-2001]

IAS-16. Two identical springs, each of stiffness K, are

assembled as shown in the given figure. The combined stiffness of the assembly is:

(a) K2 (b) 2K (c) K (d) (1/2)K

[IAS-1998]

Flat spiral Spring IAS-17. Mach List-I (Type of spring) with List-II (Application) and select the correct

answer: [IAS-2000] List-I List-II A. Leaf/Helical springs 1. Automobiles/Railways coachers B. Spiral springs 2. Shearing machines C. Belleville springs 3. Watches Codes: A B C A B C (a) 1 2 3 (b) 1 3 2 (c) 3 1 2 (d) 2 3 1

Semi-elliptical spring IAS-18. The ends of the leaves of a semi-elliptical leaf spring are made triangular in

plain in order to: [IAS 1994] (a) Obtain variable I in each leaf (b) Permit each leaf to act as a overhanging beam (c) Have variable bending moment in each leaf (d) Make Mil constant throughout the length of the leaf.



OBJECTIVE ANSWERS

GATE-1. Ans. (a) 3

4

8PD NG.d

δ =

GATE-2. Ans. (d) Spring constant (K) =ND

dGP3

4

8.=

δ or K∝ 3

1D

81020 33

2

1

1

2 =⎟⎠⎞

⎜⎝⎛=⎟⎟

⎠

⎞⎜⎜⎝

⎛=

DD

KK

GATE-3. Ans. (c) Spring constant (K) =ND

dGP3

4

8.=

δ Therefore

4dkn

∞

GATE-4. Ans. (c) Inclined it to a very low angle, dθ For equilibrium taking moment about ‘hinge’

( )l W 300W d k ld l 0 or k 500N / m2 2l 2 0.3

θ θ⎛ ⎞× − × = = = =⎜ ⎟ ×⎝ ⎠

GATE-5. Ans. (b) Initial length = lo m and stiffness = k N/m

( )

( )o

o

2 g k l 0.2

2 g 20 g k l 0.1

× = −

× + × = −

Just solve the above equations. GATE-6. Ans. (d) When a spring is cut into two, no. of coils gets halved. ∴ Stiffness of each half gets doubled. When these are connected in parallel, stiffness = 2k + 2k = 4k Therefore deflection will be ¼ times. = 2.5 mm

IES

IES-1. Ans. (a) 3

4

8PD NGd

δ =

= × = θ

θ =

= π

⎛ ⎞ ⎛ ⎞= =⎜ ⎟ ⎜ ⎟⎝ ⎠ ⎝ ⎠

∂δ = =∂

2 2 3

4

3

4

D 1T F ; U T2 2

FD TLΤ = ;2 GJ

L DN

1 FD L 4F D NU2 2 GJ GdU 8FD NF Gd

IES-1(i). Ans. (b) = 8

IES-2. Ans. (b) IES-3. Ans. (c) It is for preventing locking not for buckling.

IES-4. Ans. (c) ( )4

3

Gd 1Stiffness of sprin k so k andnwiil behalfn8D n

= ∞

IES-4(i). Ans. (c)

IES-5. Ans. (b) 21mg(h x) kx2

+ =



IES-6. Ans. (c) s 3

8PDUse kd

τπ

=

IES-7. Ans. (b) s 3

8PDUse kd

τπ

= it is independent of number of turn

IES-8. Ans. (c)

IES-9. Ans. (a) ( )

4 4

23 3Stiffness (k) ; econd spring,stiffness (k ) =

64 464 22

Gd Gd kS NR N R= =

×

IES-10. Ans. (a) IES-11. Ans. (a)

IES-12. Ans. (b) ( ) ( ) ( )( )

7 2 4 44

3 3 3

10 N / cm 2 cmGdStiffness of sprin k 100N / cm8D n 8 20 cm 25

×= = =

× ×

IES-13. Ans. (b) IES-14. Ans. (c) IES-15. Ans. (a) IES-16. Ans. (a)

IES-17. Ans. (d) 33

3

20 1 8;40 8 8 8 9

o i i io i i

i o

W R W WW So W P or W PW R

⎛ ⎞= = = = + = =⎜ ⎟⎝ ⎠

IES-18. Ans. (c) 4

3Stiffnessof spring (k) Where G and d issame64

= GdR n

3 32

2 2

1 1 1Therefore1.5675 8

60 10

= = =⎛ ⎞ ⎛ ⎞ ⎛ ⎞ ⎛ ⎞

⎜ ⎟ ⎜ ⎟⎜ ⎟ ⎜ ⎟ ⎝ ⎠ ⎝ ⎠⎝ ⎠ ⎝ ⎠

kk R n

R n IES-18a. Ans. (a) But most of the students think answer will be (b). If your calculated answer is

also (b) then read the question again and see “Two equal lengths of steel wires” is

written that means number of turns are different. And 2 11 1 2 2

1 2

7560

n DL D n D n

n Dπ π= = ∴ = =

4

3Stiffnessof spring (S) Where G and d issame64Gd

R n=

3 3 3 2

1 2 2 2 2

2 1 1 1 1

60 75 60Therefore75 60 75

S R n D nS R n D n

⎛ ⎞ ⎛ ⎞ ⎛ ⎞ ⎛ ⎞ ⎛ ⎞ ⎛ ⎞ ⎛ ⎞= = = =⎜ ⎟ ⎜ ⎟ ⎜ ⎟ ⎜ ⎟ ⎜ ⎟ ⎜ ⎟ ⎜ ⎟⎝ ⎠ ⎝ ⎠ ⎝ ⎠⎝ ⎠ ⎝ ⎠ ⎝ ⎠ ⎝ ⎠

IES-19. Ans. (b) ( )4

3

GdStiffness of spring k8D n

= 2 1

1 2

k n1 25k or 1.25n k n 20

α∴ = = =

IES-20. Ans. (a) ( )4

3

GdStiffness of spring k8D n

=

IES-21. Ans. (a) IES-22. Ans. (a) Same as [IES-1992]



IES-22(i). Ans. (a) IES-22(ii). Ans. (b) IES-23. Ans. (d)

IES-24. Ans. (d) use ( ) 21mg h x kx2

+ =

IES-25. Ans. (b) IES-26. Ans. (b) IES-27. Ans. (c) When a spring is cut into two, no. of coils gets halved. ∴ Stiffness of each half gets doubled. When these are connected in parallel, stiffness = 2k + 2k = 4k

IES-28. Ans. (c) 1 1 1 2

2 3ee

or S SS S S

= + =

IES-29. Ans. (b) 1 2W k k kδ δ δ= = +

IES-30. Ans. (b) 1 1 1 10

10 5 3= + =e

e

or SS



IES-31. Ans. (b)

IES-32. Ans. (c) The strain energy stored per spring =2

21 1. / 2 / 22 2 eq

eq

Fk x kk

⎛ ⎞= × × ⎜ ⎟⎜ ⎟

⎝ ⎠ and here total

force ‘F’ is supported by both the spring 1 and 2 therefore keq = k + k =2k IES-33. Ans. (a) Stiffness K1 of 10 coils spring = 8 N/mm ∴ Stiffness K2 of 5 coils spring = 16 N/mm Though it looks like in series but they are in parallel combination. They are not subjected

to same force. Equivalent stiffness (k) = k1 + k2 = 24 N/mm

IAS IAS-1. Ans. (a) IAS-2. Ans. (d) IAS-3. Ans. (c) It is for preventing locking not for buckling.

IAS-4. Ans. (c) ( )4

3

Gd 1Stiffness of sprin k so k andnwiil behalfn8D n

= ∞

IAS-5. Ans. (b) K=4

2 13

1 2

1 15 1.58 10

K NGd or K orD N N K N

α = = =

IAS-6. Ans. (d) ( ) ( )5 10 10 1570l Dn cd n mmπ π π= = = × × × = IAS-7. Ans. (b)

IAS-8. Ans. (a)

2 23 3

1 124 4 4

1 2

1

D ND N8PD N 4 2or 8

Gd 2dd

δδδ

⎛ ⎞⎛ ⎞⎜ ⎟⎜ ⎟

×⎝ ⎠⎝ ⎠= = = =⎛ ⎞⎜ ⎟⎝ ⎠

IAS-9. Ans. (d) Kinetic energy of block = potential energy of spring

or 22 2

1 2 2 2 1. / 400 /2 0.1

WhW h k x or k N m N mx

× ×× = = = =

IAS-10. Ans. (b) { }22 21 1 10NE kx 1 0.6 m 800Nm12 2 m

1000

⎧ ⎫⎪ ⎪⎪ ⎪= = × × − =⎨ ⎬⎛ ⎞⎪ ⎪⎜ ⎟⎪ ⎪⎝ ⎠⎩ ⎭

IAS-11. Ans. (a) Work done by the spring is = −2 21 2

1 1k x k x2 2

IAS-12. Ans. (d) ( ) { }2 2 2 22 1

1 1E k x x 1000 0.20 0.10 15Nm2 2

= − = × × − =

IAS-13. Ans. (b) IAS-14. Ans. (a)

Work done = ( )22 2 2 21 1 10N 1 10k.x 1 0.6 m 0.4 80012 2 1mm 2

1000

⎛ ⎞= × × − = × × =⎜ ⎟ ⎛ ⎞⎝ ⎠ ⎜ ⎟

⎝ ⎠

N m Jm



IAS-15. Ans. (c) 1 1 1 2

2 3ee

or S SS S S

= + =

IAS-16. Ans. (b) Effective stiffness = 2K. Due to applied force one spring will be under tension and another one under compression so total resistance force will double.

IAS-17. Ans. (b) IAS-18. Ans. (d) The ends of the leaves of a semi-elliptical leaf spring are made rectangular in plan

in order to make M/I constant throughout the length of the leaf.


Conventional Question ESE-2008 Question: A close-coiled helical spring has coil diameter D, wire diameter d and number

of turn n. The spring material has a shearing modulus G. Derive an expression for the stiffness k of the spring.

Answer: The work done by the axial force 'P' is converted into strain energy and stored in the spring.

( )( )

U= average torque

× angular displacementT = ×θ2

TLFrom the figure we get, θ =GJ

PDTorque (T)=2

4

2 3

4

length of wire (L)=πDnπdPolar moment of Inertia(J)=32

4P D nTherefore U= Gd

According to Castigliano's theorem, the displacement corresponding to force P is obtained by partially differentiating strain energy with respect to that force.

( )

2 3 3

4 4

4

3

4 8UTherefore =

PSo Spring stiffness, k =8

p D n PD nP P Gd Gd

GdD n

δ

δ

⎡ ⎤∂∂ ⎢ ⎥= =⎢ ⎥∂ ∂ ⎣ ⎦

=



Conventional Question ESE-2010 Q. A stiff bar of negligible weight transfers a load P to a combination of three

helical springs arranged in parallel as shown in the above figure. The springs are made up of the same material and out of rods of equal diameters. They are of same free length before loading. The number of coils in those three springs are 10, 12 and 15 respectively, while the mean coil diameters are in ratio of 1 : 1.2 : 1.4 respectively. Find the distance ‘x’ as shown in figure, such that the stiff bar remains horizontal after the application of load P. [10 Marks]

l l

x P

Ans. Same free length of spring before loading

The number of coils in the spring 1,2 and 3 is 10, 12 and 15 mean diameter of spring 1,2 and 3 in the ratio of 1 : 1.2 : 1.4 Find out distance x so that rod remains horizontal after loading.

Since the rod is rigid and remains horizontal after the load p is applied therefore the deflection of each spring will be same

1 2 3 (say)δ = δ = δ = δ Spring are made of same material and out of the rods of equal diameter = = = = = =1 2 3 1 2 3G G G G and d d d d Load in spring 1

δ δ δ= = =

×

4 4 4

1 3 3 31 1 1 1

Gd Gd GdP .....(1)64R n 64R 10 640R

Load in spring 2

δ δ δ= = =

× × ×

4 4 4

2 3 3 3 32 2 1 1

Gd Gd GdP .....(2)64 R n 64 (1.2) 12R 1327.10R

Load in spring 3

δ δ δ= = =

× ×

4 4 4

3 3 3 3 33 3 1 1

Gd Gd GdP .....(3)64R n 64 (1.4) 15R 2634.2R

From eqn (1) & (2)

2 1

2 1

640P P1327.1

P 0.482P

=

=



( )

= =

× + × =+ × =

+=

= + +

n

3 1 1

1

2 3

1 1

1

1 2 3

1 1

from eq (1) & (3)640P P 0.2430P

2634.2Taking moment about the line of action P

P L P 2L P.x0.4823 P L 0.2430 P 2L P.x.

0.4823 0.486 P Lx ........(4)

Ptotal load in the rod is

P=P +P +PP P .4823P 0.24=

= = =

=

1

1

1 1

30PP 1.725 P ......(5)

Equation (4) & (5)0.9683L 0.9683Lx 0.5613L

1.725 P / P 1.725x 0.5613 L

Conventional Question ESE-2008 Question: A close-coiled helical spring has coil diameter to wire diameter ratio of 6. The

spring deflects 3 cm under an axial load of 500N and the maximum shear stress is not to exceed 300 MPa. Find the diameter and the length of the spring wire required. Shearing modulus of wire material = 80 GPa.

Answer: δ

4

3,8GdPStiffness KD n

= =

( )9

3

4

80 10500 D, [ c= 6]0.03 8 6 d

, 3.6 10 ( )

dor given

n

or d n i−

× ×= =

× ×

= × −−−

static loading correcting factor(k)

0.5 0.5 k= 1+ 1 1.0833c 6

For⎛ ⎞ ⎛ ⎞⎟ ⎟⎜ ⎜= + =⎟ ⎟⎜ ⎜⎟ ⎟⎜ ⎜⎝ ⎠ ⎝ ⎠

( )

π

dπ

3

2

8PD know that =kd

8 6

We

kPC DCd

τ

τ⎡ ⎤⎢ ⎥= = =⎢ ⎥⎣ ⎦∵

3

6

1.0833 8 500 6 5.252 10 5.252300 10

D=cd=6×5.252mm=31.513mm

d m mm

Soπ

−× × ×= = × =

× ×

π π×

From, equation (i) n=14.59 15Now length of spring wire(L) = Dn = 31.513×15 mm =1.485 m

Conventional Question ESE-2007



Question: A coil spring of stiffness 'k' is cut to two halves and these two springs are assembled in parallel to support a heavy machine. What is the combined stiffness provided by these two springs in the modified arrangement?

Answer: When it cut to two halves stiffness of each half will be 2k. Springs in parallel. Total load will be shared so

Total load = W+W

δ δ δ. .(2 ) .(2 )

4 .eq

eq

or K k k

or K k

= +

=

Conventional Question ESE-2001 Question: A helical spring B is placed inside the coils of a second helical spring A ,

having the same number of coils and free axial length and of same material. The two springs are compressed by an axial load of 210 N which is shared between them. The mean coil diameters of A and B are 90 mm and 60 mm and the wire diameters are 12 mm and 7 mm respectively. Calculate the load shared by individual springs and the maximum stress in each spring.

Answer: 4

3

GdThe stiffness of the spring (k) =8D N

⎛ ⎞ ⎛ ⎞ ⎛ ⎞ ⎛ ⎞⎟ ⎟⎜ ⎜ ⎟ ⎟⎜ ⎜⎟ ⎟ = = × =⎜ ⎜ ⎟ ⎟⎜ ⎜⎟ ⎟ ⎟ ⎟⎜ ⎜ ⎜ ⎜⎟ ⎟⎜ ⎜ ⎝ ⎠ ⎝ ⎠⎝ ⎠ ⎝ ⎠

e A B4 3 4 3

A AA

B B A

Here load shared the springs are arranged in parallelEquivalent stiffness(k )=k +k

K d 12 60Hear = [As N ] 2.559K d 7 90N

D ND

B

= =+

Total load 210Let total deflection is 'x' m xEquivalet stiffness A B

NK K

( )

A210 210Load shared by spring 'A'(F ) =151N

111 2.559

Load shared by spring 'A'(F ) 210 151 59 N

= × = =⎛ ⎞ ⎛ ⎞⎟ ⎟⎜ ⎜ +⎟ ⎟+⎜ ⎜ ⎟⎟ ⎜⎜ ⎝ ⎠⎟⎜⎝ ⎠

= × = − =

AB

A

B B

K xkk

K x

3

0.5 8For static load: = 1+C π

τ⎛ ⎞⎟⎜ ⎟⎜ ⎟⎜⎝ ⎠

PDd

( )( )3max

0.5 8 151 0.0901 21.362MPa90 π 0.01212

τ

⎧ ⎫⎪ ⎪⎪ ⎪⎪ ⎪⎪ ⎪ × ×⎪ ⎪= + =⎨ ⎬⎛ ⎞⎪ ⎪ ×⎟⎪ ⎪⎜ ⎟⎪ ⎪⎜ ⎟⎜⎪ ⎪⎝ ⎠⎪ ⎪⎩ ⎭

A

( )( )3max

0.5 8 59 0.0601 27.816 MPa60 π 0.0077

τ

⎛ ⎞⎟⎜ ⎟⎜ ⎟⎜ × ×⎟⎜ ⎟= + =⎜ ⎟⎜ ⎟⎛ ⎞⎜ ⎟ ×⎟⎜ ⎟⎜ ⎟⎜ ⎟⎜ ⎟⎜ ⎟⎜ ⎝ ⎠⎝ ⎠

B

Conventional Question AMIE-1997



Question: A close-coiled spring has mean diameter of 75 mm and spring constant of 90 kN/m. It has 8 coils. What is the suitable diameter of the spring wire if maximum shear stress is not to exceed 250 MN/m2? Modulus of rigidity of the spring wire material is 80 GN/m2. What is the maximum axial load the spring can carry?

Answer: Given D 75mm; k 80kN / m; n 8= = = τ = = = ×2 2 9 2250MN / m ; G 80GN / m 80 10 N / m Diameter of the spring wire, d:

We know,

( )

( ) ( )

( )

πτ

π

δδ

= × = ×

× = × × − − −

== × × − − −

3

6 3

3

T d whereT P R16

P 0.0375 250 10 d i16

Also P kor P 80 10 ii

Using the relation:

( )δ

δ

−

−

× ×= = = × ×

× ×

= × × × × =

3314

4 9 4 4

3 144

8P 0.075 88PD n P 33.75 10Gd 80 10 d d

Substituting for in equation(ii),we getPP 80 10 33.75 10 or d 0.0128m or 12.8mmd

Maximum axial load the spring can carry P: From equation (i), we get

( ) ( )π× = × × × ∴ = =36P 0.0375 250 10 0.0128 ; P 2745.2N 2.7452kN16


13. Theories of Column

Theory at a Glance (for IES, GATE, PSU) 1. Introduction

• Strut: A member of structure which carries an axial compressive load.

• Column: If the strut is vertical it is known as column.

• A long, slender column becomes unstable when its axial compressive load reaches a value

called the critical buckling load.

• If a beam element is under a compressive load and its length is an order of magnitude larger

than either of its other dimensions such a beam is called a columns.

• Due to its size its axial displacement is going to be very small compared to its lateral

deflection called buckling.

• Buckling does not vary linearly with load it occurs suddenly and is therefore dangerous

• Slenderness Ratio: The ratio between the length and least radius of gyration.

• Elastic Buckling: Buckling with no permanent deformation.

• Euler buckling is only valid for long, slender objects in the elastic region.

• For short columns, a different set of equations must be used.

2. Which is the critical load? • At this value the structure is in equilibrium regardless of the magnitude of the angle

(provided it stays small)

• Critical load is the only load for which the structure will be in equilibrium in the disturbed

position

• At this value, restoring effect of the moment in the spring matches the buckling effect of the

axial load represents the boundary between the stable and unstable conditions.

• If the axial load is less than Pcr the effect of the moment in the spring dominates and the

structure returns to the vertical position after a small disturbance – stable condition.

• If the axial load is larger than Pcr the effect of the axial force predominates and the structure

buckles – unstable condition.

• Because of the large deflection caused by buckling, the least moment of inertia I can be

expressed as, I = Ak2

• Where: A is the cross sectional area and r is the radius of gyration of the cross sectional area,

i.e. kmin = minIA


Chapter-13 Theories of Column S K Mondal’s

• Note that the smallest radius of gyration of the column, i.e. the least moment of inertia I

should be taken in order to find the critical stress. l/ k is called the slenderness ratio, it is a measure of the column's flexibility.

3. Euler’s Critical Load for Long Column Assumptions:

(i) The column is perfectly straight and of uniform cross-section (ii) The material is homogenous and isotropic

(iii) The material behaves elastically (iv) The load is perfectly axial and passes through the centroid of the column section.

(v) The weight of the column is neglected.

Euler’s critical load,

2

2

πcr

e

EIPl

=

Where e=Equivalent length of column (1st mode of bending)

4. Remember the following table Case Diagram Pcr Equivalent

length(le)

Both ends hinged/pinned

Both ends fixed

One end fixed & other end free

2

2

π EI

2

2

4π EI2

2

2

π EI4

2


C

O/h

5

6R

Chapter-13

One end fixehinged

5. Slender

=

Sle

=

∴

crP

6. RankineRankine theo

• Short• Long

• Slend

• Cripp

• P =

d & other en

rness Rat2

2

2

2

min

π whe

π=

enderness R

=

⎛ ⎞⎜ ⎟⎝ ⎠

e

e

EIL

EA

k

e’s Crippory is appliet strut /colu

g Column (V

derness ratio

πσ

=e

k

pling Load ,

cσ=1 '⎛+ ⎜

⎝e

A

Kk

nd pinned

tio of Col2min

e

min

ere I=A k

Ratio = k

pling Loaded to both mn (valid upalid upto SR

o

2πσe

E

P

2⎞⎟⎠

Theorie

lumn

n

min k leas=

d

pto SR-40) R 120)

(σ criti=e

es of Colum

st radius of

ical stress)=

mn

gyration

crP=A

S K Mo

2

ondal’s



c2

σwhere k' = Rankine constant = depends on material & end conditionsπ E

cσ stress= crushing

• For steel columns

K’ = 1

25000for both ends fixed

= 1

12500 for one end fixed & other hinged 20 100≤ ≤e

k

7. Other formulas for crippling load (P)

• Gordon’s formula,

2

σ b = a constant, d = least diameter or breadth of bar1

=⎛ ⎞+ ⎜ ⎟⎝ ⎠

c

e

APb

d

• Johnson Straight line formula,

σ 1 c = a constant depending on material.⎡ ⎤⎛ ⎞= − ⎜ ⎟⎢ ⎥⎝ ⎠⎣ ⎦e

cP A ck

• Johnson parabolic formulae :

where the value of index ‘b' depends on the end conditions.

• Fiddler’s formula,

( ) ( )2

cσ σ σ σ 2 σ σ⎡ ⎤= + − + −⎢ ⎥⎣ ⎦

c e e c eAP cC

2

e 2πwhere, σ =

⎛ ⎞⎜ ⎟⎝ ⎠

e

E

k

8. Eccentrically Loaded Columns • Secant formula

max 2σ 1 sec2

⎡ ⎤⎛ ⎞= +⎢ ⎥⎜ ⎟⎝ ⎠⎣ ⎦

c eeyP PA k k EA

Where maxσ =maximum compressive stress

P = load

u

PP

PP

M M



c

A = Area of c/sy = Distance of the outermost fiber in compression from the NAe = Eccentricity of the load

el = Equivalent length

Ik = Radius of gyration =A

Modulus of elasticity of the material=E

e. .

2k

Where M = Moment introduced.

⎛ ⎞= ⎜ ⎟⎜ ⎟

⎝ ⎠

PM P e SecEA

• Prof. Perry’s Formula

max 12

σ σ1 1σ σ

⎛ ⎞⎛ ⎞− − =⎜ ⎟⎜ ⎟

⎝ ⎠⎝ ⎠d c

d e

e yk

maxWhere σ maximum compressive stress=

d

2

2

Loadσc/s areaEuler's loadσ

/ areaπ'

= =

= =

= =

ee

ee

PAPA c s

EIp Euler s load

1

' Versine at mid-length of column due to initial curvaturee = Eccentricity of the loade ' 1.2

distance of outer most fiber in compression form the NAk = Radius of gyration

=

= +=c

e

e ey

If maxσ is allowed to go up to fσ (permssible stress)

Then, 12η = ce y

k

2

f

σ σ (1 ) σ σ (1 )σ σ σ

2 2f e f e

d e

η η+ + + +⎧ ⎫= − −⎨ ⎬

⎩ ⎭

• Perry-Robertson Formula



0.003

σ σ 1 0.003 σ σ (1 0.003σ σ σ

2 2

η ⎛ ⎞= ⎜ ⎟⎝ ⎠

⎛ ⎞ ⎧ ⎫+ + + +⎜ ⎟ ⎪ ⎪⎝ ⎠= − −⎨ ⎬⎪ ⎪⎩ ⎭

e

e ef e f e

d e f

k

k k

9. ISI’s Formula for Columns and Struts

• For e

k=0 to 160

'

σ

1 0.2sec4

=⎛ ⎞×+ ⎜ ⎟⎝ ⎠

y

ce c

fosPfos p

k E

Where, Pc = Permissible axial compressive stress Pc’ = A value obtained from above Secant formula

yσ = Guaranteed minimum yield stress = 2600 kg/cm2 for mild steel

fos = factor of safety = 1.68

elk= Slenderness ratio

E = Modulus of elasticity = 6 22.045 10 /kg cm× for mild steel

• For 160elk>





Strength of Column GATE-1. The rod PQ of length L and with

flexural rigidity EI is hinged at both ends. For what minimum force F is it expected to buckle?

(a) 2

2

LEIπ

(b) 2

22 EILπ

(c) 2

2

2LEIπ

(b) 2

2

2LEIπ

[GATE-2008]

Equivalent Length GATE-2. The ratio of Euler's buckling loads of columns with the same parameters

having (i) both ends fixed, and (ii) both ends hinged is: [GATE-1998; 2002; IES-2001, GATE-2012]

(a) 2 (b) 4 (c) 6 (d) 8

Euler's Theory (For long column) GATE-3. A pin-ended column of length L, modulus of elasticity E and second moment of

the cross-sectional area I is loaded centrically by a compressive load P. The critical buckling load (Pcr) is given by: [GATE-2006]

(a) 2 2crEIP

Lπ= (b)

2

23crEIPL

π= (c) 2crEIPLπ= (d)

2

2crEIP

Lπ=

GATE-4. What is the expression for the crippling load for a column of length ‘l’ with one

end fixed and other end free? [IES-2006; GATE-1994]

(a) 2

22 EIP

lπ= (b)

2

24EIPl

π= (c) 2

24 EIP

lπ= (d)

2

2EIP

lπ=

GATE-4A. The piston rod of diameter 20 mm and length 700 mm in a hydraulic cylinder is

subjected to a compressive force of 10 KN due to the internal pressure. The end conditions for the rod may be assumed as guided at the piston end and hinged at the other end. The Young’s modulus is 200 GPa. The factor of safety for the piston rod is (a) 0.68 (b) 2.75 (c) 5.62 (d) 11.0 [GATE-2007]

GATE-4(ii)A steel column, pinned at both ends, has a buckling load of 200 kN. If the

column is restrained against lateral movement at its mid-height, its buckling load will be [CE: GATE-2007]

(a) 200 kN (b) 283 kN (c) 400 kN (d) 800 kN



GATE-5. A long structural column (length = L) with both ends hinged is acted upon by an axial compressive load P. The differential equation governing the bending of column is given by:

2

2EI Pd y ydx

= − [CE: GATE-2003]

where y is the structural lateral deflection and EI is the flexural rigidity. The first critical load on column responsible for its buckling is given by

(a) 2

2EI

Lπ (b)

2

22 EILπ

(c) 2

22 EI

Lπ (d)

2

24 EI

Lπ

GATE-6. A thin-walled long cylindrical tank of inside radius r is subjected simultaneously to internal gas pressure p and axial compressive force F at its ends. In order to produce ‘pure shear’ state of stress in the wall of the cylinder, F should be equal to

(a) 2p rπ (b) 22p rπ [CE: GATE-2006] (c) 23p rπ (d) 24p rπ GATE-7. Cross-section of a column consisting of two steel strips, each of thickness t and width b is

shown in the figure below. The critical loads of the column with perfect bond and without

bond between the strips are P and 0P respectively. The ratio 0

PP

is [CE: GATE-2008]

t

b

t

(a) 2 (b) 4 (c) 6 (d) 8 GATE-8. A rigid bar GH of length L is supported by a hinge and a spring of stiffness K as

shown in the figure below. The buckling load, P ,cr for the bar will be

L

H K P

G

[CE: GATE-2008] (a) 0.5 KL (b) 0.8 KL (c) 1.0 KL (d) 1.2 KL GATE-9. This sketch shows a column with a pin at the base and rollers at the top. It is

subjected to an axial force P and a moment M at mid height. The reaction(s) at R is/are



O

P

M

R

h2

h2

[CE: GATE-2012]

(a) a-vertical force equal to P (b) a vertical force equal to P2

(c) a vertical force equal to P and a horizontal force equal to Mh

(d) a vertical force equal to P2

and a horizontal force equal to Mh


Classification of Column IES-1. A structural member subjected to an axial compressive force is called

[IES-2008] (a) Beam (b) Column (c) Frame (d) Strut IES-2. Which one of the following loadings is considered for design of axles? (a) Bending moment only [IES-1995] (b) Twisting moment only (c) Combined bending moment and torsion (d) Combined action of bending moment, twisting moment and axial thrust. IES-2a An axle is a machine part that is subjected to: [IES-2011]

(a) Transverse loads and bending moment (b) Twisting moment only (c) Twisting moment an axial load (d) Bending moment and axial load

IES-3. The curve ABC is the Euler's

curve for stability of column. The horizontal line DEF is the strength limit. With reference to this figure Match List-I with List-II and select the correct answer using the codes given below the lists:

List-I List-II (Regions) (Column specification) A. R1 1. Long, stable B. R2 2. Short C. R3 3. Medium D. R4 4. Long, unstable

[IES-1997] Codes: A B C D A B C D



(a) 2 4 3 1 (b) 2 3 1 4 (c) 1 2 4 3 (d) 2 1 3 4 IES-4. Mach List-I with List-II and select the correct answer using the codes given

below the lists: [IAS-1999] List-I List-II A. Polar moment of inertia of section 1. Thin cylindrical shell B. Buckling 2. Torsion of shafts C. Neutral axis 3. Columns D. Hoop stress 4. Bending of beams Codes: A B C D A B C D (a) 3 2 1 4 (b) 2 3 4 1 (c) 3 2 4 1 (d) 2 3 1 4

Strength of Column IES-5. Slenderness ratio of a column is defined as the ratio of its length to its (a) Least radius of gyration (b) Least lateral dimension [IES-2003] (c) Maximum lateral dimension (d) Maximum radius of gyration IES-6. Assertion (A): A long column of square cross section has greater buckling

stability than a similar column of circular cross-section of same length, same material and same area of cross-section with same end conditions.

Reason (R): A circular cross-section has a smaller second moment of area than a square cross-section of same area. [IES-1999; IES-1996]


Equivalent Length IES-6(i). The end conditions of a column for which length of column is equal to the

equivalent length are [IES-2013] (a) Both the ends are hinged (b) Both the ends are fixed (c) One end fixed and other end free (d) One end fixed and other end hinged IES-7. Four columns of same material and same length are of rectangular cross-

section of same breadth b. The depth of the cross-section and the end conditions are, however different are given as follows: [IES-2004]

Column Depth End conditions 1 0.6 b Fixed-Fixed 2 0.8 b Fixed-hinged 3 1.0 b Hinged-Hinged 4 2.6 b Fixed-Free Which of the above columns Euler buckling load maximum? (a) Column 1 (b) Column 2 (c) Column 3 (d) Column 4 IES-8. Match List-I (End conditions of columns) with List-II (Equivalent length in

terms of length of hinged-hinged column) and select the correct answer using the codes given below the Lists: [IES-2000]

List-I List-II A. Both ends hinged 1. L B. One end fixed and other end free 2. L/ 2 C. One end fixed and the other pin-pointed 3. 2L D. Both ends fixed 4. L/2 Code: A B C D A B C D (a) 1 3 4 2 (b) 1 3 2 4 (c) 3 1 2 4 (d) 3 1 4 2 IES-9. The ratio of Euler's buckling loads of columns with the same parameters

having (i) both ends fixed, and (ii) both ends hinged is:



[GATE-1998; 2002; IES-2001] (a) 2 (b) 4 (c) 6 (d) 8

Euler's Theory (For long column) IES-10. What is the expression for the crippling load for a column of length ‘l’ with one

end fixed and other end free? [IES-2006; GATE-1994]

(a) 2

2

2 EIPlπ= (b)

2

24EIPl

π= (c) 2

2

4 EIPlπ= (d)

2

2

EIPl

π=

IES-10(i). The buckling load for a column hinged at both ends is 10 kN. If the ends are

fixed, the buckling load changes to [IES-2012] (a) 40 kN (b) 2.5 kN (c) 5 kN (d) 20 kN

IES-10(ii). For the case of a slender column of length L and flexural rigidity EI built in at

its base and free at the top, the Euler’s critical buckling load is [IES-2012] 4 2 4 IES-11. Euler's formula gives 5 to 10% error in crippling load as compared to

experimental results in practice because: [IES-1998] (a) Effect of direct stress is neglected (b) Pin joints are not free from friction (c) The assumptions made in using the formula are not met in practice (d) The material does not behave in an ideal elastic way in tension and compression IES-12. Euler's formula can be used for obtaining crippling load for a M.S. column with

hinged ends.

Which one of the following conditions for the slenderness ratio lk

is to be

satisfied? [IES-2000]

(a) 5 8lk

< < (b) 9 18lk

< < (c) 19 40lk

< < (d) 80lk≥

IES-13. If one end of a hinged column is made fixed and the other free, how much is the

critical load compared to the original value? [IES-2008] (a) ¼ (b) ½ (c) Twice (d) Four times IES-14. If one end of a hinged column is made fixed and the other free, how much is the

critical load compared to the original value? [IES-2008] (a) ¼ (b) ½ (c) Twice (d) Four times IES-15. Match List-I with List-II and select the correct answer using the code given

below the Lists: [IES-1995; 2007; IAS-1997] List-I (Long Column) List-II (Critical Load) A. Both ends hinged 1. π 2EI/4l2

B. One end fixed, and other end free 2. 4 π 2EI/ l2 C. Both ends fixed 3. 2 π 2EI/ l2 D. One end fixed, and other end hinged 4. π 2EI/ l2 Code: A B C D A B C D (a) 2 1 4 3 (b) 4 1 2 3 (c) 2 3 4 1 (d) 4 3 2 1 IES-16. The ratio of the compressive critical load for a long column fixed at both the

ends and a column with one end fixed and the other end free is: [IES-1997] (a) 1 : 2 (b) 1: 4 (c) 1: 8 (d) 1: 16 IES-17. The buckling load will be maximum for a column, if [IES-1993]



(a) One end of the column is clamped and the other end is free (b) Both ends of the column are clamped (c) Both ends of the column are hinged (d) One end of the column is hinged and the other end is free IES-18. If diameter of a long column is reduced by 20%, the percentage of reduction in

Euler buckling load is: [IES-2001, 2012] (a) 4 (b) 36 (c) 49 (d) 59 IES-19. A long slender bar having uniform rectangular cross-section 'B x H' is acted

upon by an axial compressive force. The sides B and H are parallel to x- and y-axes respectively. The ends of the bar are fixed such that they behave as pin-jointed when the bar buckles in a plane normal to x-axis, and they behave as built-in when the bar buckles in a plane normal to y-axis. If load capacity in either mode of buckling is same, then the value of H/B will be: [IES-2000]

(a) 2 (b) 4 (c) 8 (d) 16 IES-20. The Euler's crippling load for a 2m long slender steel rod of uniform cross-

section hinged at both the ends is 1 kN. The Euler's crippling load for 1 m long steel rod of the same cross-section and hinged at both ends will be: [IES-1998]

(a) 0.25 kN (b) 0.5 kN (c) 2 kN (d) 4 kN IES-20(i). Determine the ratio of the buckling strength of a solid steel column to that of a

hollow column of the same material having the same area of cross section. The internal diameter of the hollow column is half of the external diameter. Both column are of identical length and are pinned or hinged at the ends: [IES-2013]

(a) P 2P 5

s

h

= (b) P 3P 5

s

h

= (c) P 4P 5

s

h

= (d) P 1P

s

h

=

IES-21. If σc and E denote the crushing stress and Young's modulus for the material of

a column, then the Euler formula can be applied for determination of cripping load of a column made of this material only, if its slenderness ratio is:

(a) More than / cEπ σ (b) Less than / cEπ σ [IES-2005]

(c) More than 2

c

Eπσ⎛ ⎞⎜ ⎟⎝ ⎠

(d) Less than 2

c

Eπσ⎛ ⎞⎜ ⎟⎝ ⎠

IES-22. Four vertical columns of same material, height and weight have the same end

conditions. Which cross-section will carry the maximum load? [IES-2009] (a) Solid circular section (b) Thin hollow circular section (c) Solid square section (d) I-section

Rankine's Hypothesis for Struts/Columns IES-23. Rankine Gordon formula for buckling is valid for [IES-1994] (a) Long column (b) Short column (c) Short and long column (d) Very long column

Prof. Perry's formula IES-24. Match List-I with List-II and select the correct answer using the code given

below the lists: [IES-2008] List-I (Formula/theorem/ method) List-II (Deals with topic) A. Clapeyron's theorem 1. Deflection of beam B. Maculay's method 2. Eccentrically loaded column C. Perry's formula 3. Riveted joints 4. Continuous beam



Code: A B C A B C (a) 3 2 1 (b) 4 1 2 (c) 4 1 3 (d) 2 4 3


Classification of Column IAS-1. Mach List-I with List-II and select the correct answer using the codes given

below the lists: [IAS-1999] List-I List-II A. Polar moment of inertia of section 1. Thin cylindrical shell B. Buckling 2. Torsion of shafts C. Neutral axis 3. Columns D. Hoop stress 4. Bending of beams Codes: A B C D A B C D (a) 3 2 1 4 (b) 2 3 4 1 (c) 3 2 4 1 (d) 2 3 1 4

Strength of Column IAS-2. Assertion (A): A long column of square cross-section has greater buckling

stability than that of a column of circular cross-section of same length, same material, same end conditions and same area of cross-section. [IAS-1998]

Reason (R): The second moment of area of a column of circular cross-section is smaller than that of a column of square cross section having the same area.

(a) Both A and R are individually true and R is the correct explanation of A (b) Both A and R are individually true but R is NOT the correct explanation of A (c) A is true but R is false (d) A is false but R is true IAS-3. Which one of the following pairs is not correctly matched? [IAS-2003] (a) Slenderness ratio : The ratio of length of the column to the least radius of gyration (b) Buckling factor : The ratio of maximum load to the permissible axial load on the

column (c) Short column : A column for which slenderness ratio < 32 (d) Strut : A member of a structure in any position and carrying an axial

compressive load

Equivalent Length IAS-4. A column of length 'I' is fixed at its both ends. The equivalent length of the

column is: [IAS-1995] (a) 2 l (b) 0.5 l (c) 2 l (d) l IAS-5. Which one of the following statements is correct? [IAS-2000] (a) Euler's formula holds good only for short columns (b) A short column is one which has the ratio of its length to least radius of gyration

greater than 100 (c) A column with both ends fixed has minimum equivalent or effective length (d) The equivalent length of a column with one end fixed and other end hinged is half

of its actual length



Euler's Theory (For long column) IAS-6. For which one of the following columns, Euler buckling load =

2

2

4 EIlπ

?

(a) Column with both hinged ends [IAS-1999; 2004] (b) Column with one end fixed and other end free (c) Column with both ends fixed (d) Column with one end fixed and other hinged IAS-7. Assertion (A): Buckling of long columns causes plastic deformation. [IAS-2001] Reason (R): In a buckled column, the stresses do not exceed the yield stress. (a) Both A and R are individually true and R is the correct explanation of A (b) Both A and R are individually true but R is NOT the correct explanation of A (c) A is true but R is false (d) A is false but R is true IAS-8. Match List-I with List-II and select the correct answer using the code given

below the Lists: [IES-1995; 2007; IAS-1997] List-I (Long Column) List-II (Critical Load) A. Both ends hinged 1. π 2EI/4l2

B. One end fixed, and other end free 2. 4 π 2EI/ l 2 C. Both ends fixed 3. 2 π 2EI/ l 2 D. One end fixed, and other end hinged 4. π 2EI/ l 2 Code: A B C D A B C D (a) 2 1 4 3 (b) 4 1 2 3 (c) 2 3 4 1 (d) 4 3 2 1



OBJECTIVE ANSWERS

GATE-1. Ans. (b) Axial component of the force FPQ = F Sin 450

We know for both end fixed column buckling load (P) = 2

2

LEIπ

and 0Fsin45 = P or F =2

2

2 EILπ

GATE-2. Ans. (b) Euler’s buckling loads of columns

( )

( )

2

2

2

2

4 EI1 both ends fixedl

EI2 both ends hingedl

π

π

=

=

GATE-3. Ans. (d) GATE-4. Ans. (b) GATE-4A. Ans. (c)

GATE-4(i). Ans. (c) GATE-4(ii). Ans.(d) When both ends are hinged, the buckling load is given by

π=2

2EIP

Lcr

⇒ π=2

2EI200

L

When the lateral movement at the mid-height is not available, then buckling load

π=2

21

EI(L )

Where =1LL2

π= = × =2

24 EI 4 200 800 kN

L

GATE-5. Ans. (a)

The critical load, π=2 2

2EIP

Lcn

For first critical load, n = 1

∴ π=1

2

2EIP

Lc

GATE-6. Ans. (c)

Hoop stress, θσ = prt



Longitudinal stress, σ = −πF

2 2zprt rt

Now, for pure shear state, σz should be compressive and is equal to θσ . ∴ θσ = − σz

⇒ = − +πF

2 2pr prt t rt

⇒ =π

3 F2 2prt rt

⇒ = π 2F 3 pr GATE-7. Ans. (b) We know that critical load for a column is proportional to moment of inertia irrespective

of end conditions of the column i.e. ∝P Icr When the steel strips are perfectly bonded, then

×= =3 3(2 ) 8P

12 12pbb t bt

When the steel strips are not bonded, then

= × =3 32I 2

12 12wbbt bt

∴ =

3

30

8P 12P 2

12

bt

bt

⇒ =0

P 4P

GATE-8. Ans. (c) Let the deflection in the spring be δ and force in the spring be F. Taking moments about G, we get × δ = ×P F Lcr [But F = δK ]

⇒ δ ×=δ

K LPcr

⇒ =P KLcr

G

H

δ Pcr

δ

Pcr

L

GATE-9. Ans. (c)



Q

P

M

R

h2

h2

FH

FV YF 0Σ = ⇒ VF P 0− = ⇒ VF P= QM 0Σ = ⇒ HF . M 0h − =

⇒ HMFh

=

IES IES-1. Ans. (d) A machine part subjected to an axial compressive force is called a strut. A strut may

be horizontal, inclined or even vertical. But a vertical strut is known as a column, pillar or stanchion.

The term column is applied to all such members except those in which failure would be by simple or pure compression. Columns can be categorized then as:

1. Long column with central loading 2. Intermediate-length columns with central loading 3. Columns with eccentric loading 4. Struts or short columns with eccentric loading IES-2. Ans. (a) Axle is a non-rotating member used for supporting rotating wheels etc. and do not

transmit any torque. Axle must resist forces applied laterally or transversely to their axes. Such members are called beams.

IES-2a Ans. (a) Axle is a non-rotating member used for supporting rotating wheels etc. and do not transmit any torque. Axle must resist forces applied laterally or transversely to their axes. Such members are called beams.

IES-3. Ans. (b) IES-4. Ans. (b) IES-5. Ans. (a) IES-6. Ans. (a) IES-6(i). Ans. (a) IES-7. Ans. (b) IES-8. Ans. (b) IES-9. Ans. (b) Euler’s buckling loads of columns

( )

( )

2

2

2

2

4 EI1 both ends fixedl

EI2 both ends hingedl

π

π

=

=

IES-10. Ans. (b)



IES-10(i). Ans. (a) IES-10(ii). Ans. (d) IES-11. Ans. (c) IES-12. Ans. (d) IES-13. Ans. (a) Critical Load for both ends hinged = π 2EI/ l 2 And Critical Load for one end fixed, and other end free = π 2EI/4l2

IES-14. Ans. (a) Original load = 2

2EI

Iπ

When one end of hinged column is fixed and other free. New Le = 2L

∴ New load = ( )

2 2

2 2EI EI 1 Original value

44L2Lπ π= = ×

IES-15. Ans. (b) IES-16. Ans. (d) Critical Load for one end fixed, and other end free is π 2EI/4l2 and both ends fixed

is 4 π 2EI/ l 2 IES-17. Ans. (b) Buckling load of a column will be maximum when both ends are fixed

IES-18. Ans. (d) 2

2

π= EIPL

4P I or P d∞ ∞ or ( )4 4 4

4

d dp p 0.8d1 0.59p dd

′−′− ⎛ ⎞= = − =⎜ ⎟⎝ ⎠

IES-19. Ans. (a) 2

2

π=xxEIP

L and

2

2

4π ′=yy

EIPL

as xx yyP P= then 3 3BH HB HI 4I or 4 or 2

12 12 B′= = × =

IES-20. Ans. (d) For column with both ends hinged, P =2

2EI

lπ

. If ‘l’ is halved, P will be 4 times.

IES-20(i). Ans. (b) IES-21. Ans. (a) For long column PEuler < Pcrushing

or 22 2 2 2

c c c2 2ce e

EI EAK le E leA or A or or E /k kl l

π π πσ σ π σσ

⎛ ⎞< < > >⎜ ⎟⎝ ⎠

IES-22. Ans. (b) IES-23. Ans. (c) IES-24. Ans. (b)

IAS IAS-1. Ans. (b) IAS-2. Ans. (a) IAS-3. Ans. (b) Buckling factor: The ratio of equivalent length of the column to the least radius of

gyration. IAS-4. Ans. (b) IAS-5. Ans. (c) A column with both ends fixed has minimum equivalent effective length (l/2) IAS-6. Ans. (c) IAS-7. Ans. (d) And Critical Load for one end fixed, and other end free = π 2EI/4l2 IAS-8. Ans. (b)

Previous Conventional Questions with Answers Conventional Question ESE-2001, ESE 2000 Question: Differentiate between strut and column. What is the general expression used

for determining of their critical load? Answer: Strut: A member of structure which carries an axial compressive load. Column: If the strut is vertical it is known as column.



For strut failure due to compression or force

σ =cCompressive

Area

If c ycσ σ> it fails.

Euler's formula for column( )2

2

π=C

e

EIP

Conventional Question ESE-2009 Q. Two long columns are made of identical lengths ‘l’ and flexural rigidities ‘EI’.

Column 1 is hinged at both ends whereas for column 2 one end is fixed and the other end is free.

(i) Write the expression for Euler’s buckling load for column 1. (ii) What is the ratio of Euler’s buckling load of column 1 to that column 2? [ 2 Marks] Ans. (i)

( )2 2

1 22 2EI EIP ; P right

L 4Lπ π= =

eForcolumnl,bothendhinged l L=

(ii)

Conventional Question ESE-2010 Q. The piston rod of diameter 20 mm and length 700 mm in a hydraulic cylinder is

subjected to a compressive force of 10 kN due to internal pressure. The piston end of the rod is guided along the cylinder and the other end of the rod is hinged at the cross-head. The modulus of elasticity for piston rod material is 200 GPa. Estimate the factor of safety taken for the piston rod design. [2 Marks]

Ans.

20mm PP

PσA

= ; PLδAE

= ; e 2= ;

2

e 2e

EIP π= (considering one end of the column is fixed and

other end is hinged) Pe = Euler Crippling load Compressive load, c cP σ Area= × = 10 kN

Euler’s load, ( ) ( )2 9 4

e 2

2 200 10 0.020 / 64P

(0.7)π × × × π ×

= = 63.278 kN

F.S = Euler 's loadCompressiveload

F.S = 63.278 6.3

10=

Conventional Question ESE-1999 Question: State the limitation of Euler's formula for calculating critical load on

columns Answer: Assumptions: (i) The column is perfectly straight and of uniform cross-section (ii) The material is homogenous and isotropic (iii) The material behaves elastically (iv) The load is perfectly axial and passes through the centroid of the column section.

1

2

P 4P

=



(v) The weight of the column is neglected. Conventional Question ESE-2007 Question: What is the value of Euler's buckling load for an axially loaded pin-ended

(hinged at both ends) strut of length 'l' and flexural rigidity 'EI'? What would be order of Euler's buckling load carrying capacity of a similar strut but fixed at both ends in terms of the load carrying capacity of the earlier one?

Answer: From Euler's buckling load formula,

π2

C 2Critical load (P )e

EI=

Equivalent length ( ) for both end hinged = for both end fixed.2e =

π2

c 2So for both end hinged (P )behEI

=

( )π π2 2

c 2 2

4and for both fixed (P )

2bef

EI EI= =

Conventional Question ESE-1996 Question: Euler's critical load for a column with both ends hinged is found as 40 kN.

What would be the change in the critical load if both ends are fixed? Answer: We know that Euler's critical laod,

PEuler=2

2

π

e

EI [Where E = modulus of elasticity, I = least moment of inertia

equivalent lengthe = ] For both end hinged ( e) = And For both end fixed ( e) = /2

2π

π π

. . . 2

2 2

Euler . . . 2 2

( ) =40kN(Given)

and (P ) = 4 4 40 160( / 2)

Euler b e h

b e F

EIP

EI EI kN

∴ =

= × = × =

Conventional Question ESE-1999 Question: A hollow cast iron column of 300 mm external diameter and 220 mm internal

diameter is used as a column 4 m long with both ends hinged. Determine the safe compressive load the column can carry without buckling using Euler's formula and Rankine's formula

E = 0.7×105 N/mm2, FOS = 4, Rankine constant (a) = 1/1600 Crushing Stress (σc ) = 567 N/mm2

Answer: Given outer diameter of column (D) = 300 mm = 0.3 m. Inner diameter of the column (d) = 220 mm = 0.22 m. Length of the column ( ) = 4 m End conditions is both ends hinged. Therefore equivalent length ( e ) = = 4 m.

Yield crushing stress (σc ) = 567 MPa = 567×106 N/m2 Rankine constant (a) = 1/ 1600 and E = 0.7×105 N/mm2 = 70 x 109 N/m2



( )

π π

π

π4π π

4 4 4 4 4 4

4 42 22 2

2 2

2 2 2 2 2

Moment of Inertia(I) ( ) 0.3 0.22 2.826 1064 64

0.3 0.2264 0.09316 16( )

Area(A) ( ) (0.3 0.22 ) 0.032674 4

D d m

D dI D d mA D d

D d m

−⎡ ⎤= − = − = ×⎢ ⎥⎣ ⎦

− ++= = = =

−

= − = − =

2π π

Euler2 9 4

2 2

(i) Euler's buckling load, P

(70 10 ) (2.826 10 ) 12.2MN4

P 12.2Safe load = 3.05fos 4

Eulere

Euler

EIP

MN

−× × × ×= = =

∴ = =

( )σ

Rankine

6

Rankine 2 2

Rankine

(ii)Rankine's buckling load, P

567×10 0.03267. P = = 8.59 MN1 41+1 .

1600 0.093P 8.59 load = 2.148

fos 4

c

e

A

ak

Safe MN

×=

⎛ ⎞ ⎛ ⎞⎟ ⎟⎜ ⎜×+ ⎟ ⎟⎜ ⎜⎟ ⎟⎜⎟⎜ ⎝ ⎠⎝ ⎠

∴ = =

Conventional Question ESE-2008 Question: A both ends hinged cast iron hollow cylindrical column 3 m in length has a

critical buckling load of P kN. When the column is fixed at both the ends, its critical buckling load raise by 300 kN more. If ratio of external diameter to internal diameter is 1.25 and E = 100 GPa determine the external diameter of column.

Answer: 2

2ce

EIPI

π=

2

2

For both end hinged columnEIP= ( )

Liπ

−−−

( )2 2

2 2

For both end fixed column4P+300= ( )

2

EI EI iiLL

π π= −−−

(ii) by (i) we getP+300 4 or P=100kN

P

Dividing

=

( )

( )

24 4

2

3 24 4 5

2 9

Moment of inertia of a hollow cylinder c/s is

64100 10 364 1.8577 10

100 10

PLI D dE

orD d

ππ

π π−

= − =

×− = = ×

× ×



Conventional Question AMIE-1996 Question: A piston rod of steam engine 80 cm long in subjected to a maximum load of 60

kN. Determine the diameter of the rod using Rankine's formula with permissible compressive stress of 100 N/mm2. Take constant in Rankine's

formula as 1

7500for hinged ends. The rod may be assumed partially fixed

with length coefficient of 0·6. Answer: Given: 3 2

cl 80 cm 800mm ;P 60kN 60 10 N, 100N / mm ;σ= = = = × =

1a for hinged ends; length coefficient 0.6

7500= =

To find diameter of the rod, d: Use Rankine’s formula

c2

e

APl1 ak

σ=

⎛ ⎞+ ⎜ ⎟⎝ ⎠

eHere l 0.6l 0.6 800 480 mm [ length coefficient 0.6]= = × = =∵

4

2

dI d64kA 4d

4

π

π= = =

2

32

100 d460 10

1 48017500 d / 4

π⎛ ⎞× ⎜ ⎟⎝ ⎠∴ × =⎡ ⎤+ ⎢ ⎥⎣ ⎦

Solving the above equation we get the value of ‘d’ Note: Unit of d comes out from the equation will be mm as we put the equivalent

length in mm. =or d 33.23mm Conventional Question ESE-2005 Question: A hollow cylinder CI column, 3 m long its internal and external diameters as

80 mm and 100 mm respectively. Calculate the safe load using Rankine formula: if

(i) Both ends are hinged and (ii) Both ends are fixed. Take crushing strength of material as 600 2/N mm , Rankine constant 1/1600

and factor of safety = 3.

Answer: π 4 4 4 6 4Moment of Inertia (I)= (0.1 0.08 ) 2.898 10

64m m−− = ×

44 5

D D 1.25 or d =d 1.25-5

1 D 1 1.8577 101.25

D=0.0749 m = 74.9 mm

given

or

or

−

=

⎡ ⎤⎛ ⎞⎢ ⎥⎟⎜− = ×⎟⎜⎢ ⎥⎟⎜⎝ ⎠⎢ ⎥⎣ ⎦


C

CQ

A

Chapter-13

ConventionQuestion:

Answer:

Area( )

Radius of

=1

Rankine

A

P

=

(i)

=2

Safe load

(ii) For bo

RankineP

loadSafe

nal QuestiA slenderfree end.maximumexceed th

Above figuand eccentLet y be thdeflection aThe bendin

(π

σ

2

2

0.14

f gyration (

. ;c

e

A

ak

= −

⎛ ⎞⎟⎜+ ⎟⎜ ⎟⎜⎝ ⎠

(600

Rank

10=

11

261.026kNPd (P)=FOS

×

⎛⎜+⎜⎜⎝

(oth end fix

600

1e

×=

+

RankPd (P)=FOS

ion AMIE- column is Working

m length of he eccentric

ure shows a ric load P is

he deflectionat A. ng moment a

Theorie

)20.08 2

I(k) =A

[ = eque

− =

=

) (6

ine

2.827

1 3600 0.0

N2612

S 3

×

⎞ ⎛⎟ ⎜×⎟ ⎜⎟ ⎜⎠ ⎝

=

)e

6

xed,

10 (2.8

11600 0

=

×

⎛⎜+ ×⎜⎜⎝

kine 714.8S 3

=

-1997 built-in atfrom the

f column sucity of load

slender colu applied at t

n at any sect

at the sectio

es of Colum

2.8274 10

2.8982.8274

uivalent len

×

××

)3

2

4 10;

3032

6 87.09

−×

⎞⎟⎟⎟⎠

=

3

2

1.52274 10

1.50.032

m−

=

×

⎞⎟⎟⎟⎠

8 238.27=

t one end afirst prin

uch that thding.

umn of lengtthe free end tion XX dist

n XX is give

mn3 2

6

3

0

10 0.10

ngth]

m−

−

−

×=

×

[ = l = 3e

kN

)714.8k=

7kN

and an eccenciples finhe deflectio

th ‘I’. The coA.

tant x from

en by

.032m

m for both

kN

entric load nd the expon of the fr

olumn is bu

the fixed en

S K Mo

h end hing

is applied pression foree end do

ilt in at one

nd B. Let δ

ondal’s

ed]

at the or the oes not

e end B

be the



( ) ( )

( ) ( )

δ

δ δ

= + − − − − −

+ = + + = +

2

2

2 2

2 2

d yEI P e y idxd y d y P PEI Py P e or y e

EI EIdx dx

The solution to the above differential equation is

( ) ( )

( )( )

1 2

1 2

1 2

1

P Py C cos x C sin x e iiEI EI

Where C and C are the cons tan ts.At the end B,x 0 and y 0

0 C cos 0 C sin0 e

or C e

δ

δδ

⎡ ⎤ ⎡ ⎤= + + + − − −⎢ ⎥ ⎢ ⎥

⎢ ⎥ ⎢ ⎥⎣ ⎦ ⎣ ⎦

= =∴ = + + +

= − +

( )

1 2

Differentiating equation ii we get

dy P P P PC sin x C cos xdx EI EI EI EI

⎡ ⎤ ⎡ ⎤= − +⎢ ⎥ ⎢ ⎥

⎢ ⎥ ⎢ ⎥⎣ ⎦ ⎣ ⎦

( ) 2

2

Again,at the fixed end B,dyWhen x 0, 0dx

P P0 e 0 C cos0EI EI

or C 0

δ

= =

∴ = + × +

=

( )

( ) ( )

( )

At the free end A,x ,ySubstituting for x and y in equation ii ,we have

Pe cos eEI

P ecos iiiEI e

δ

δ δ δ

δ

= =

⎡ ⎤= − + = +⎢ ⎥

⎣ ⎦⎡ ⎤

∴ = − − −⎢ ⎥ +⎣ ⎦

It is mentioned in the problem that the deflection of the free end does not exceed the eccentricity. It means that δ = e

Substituting this value in equation (iii), we have

1

P e 1cosEI e 2

P 1cosEI 2 3

EI3 P

δ

π

π

−

⎡ ⎤= =⎢ ⎥ +⎣ ⎦

⎛ ⎞∴ = =⎜ ⎟⎝ ⎠

∴ =

Conventional Question ESE-2005 Question: A long strut AB of length ' ' is of uniform section throughout. A thrust P is

applied at the ends eccentrically on the same side of the centre line with eccentricity at the end B twice than that at the end A. Show that the maximum bending moment occurs at a distance x from the end A,

Where, tan(kx)= 2 cos P and k=

sin EIk

k−


C

An

CQ

A

CQ

Chapter-13 nswer: L

b

o

o

∴

CyIA

ConventionQuestion:

Answer:

ConventionQuestion:

Let at a distbeam is y

2

2

2

2

22

2

d yEIdx

d y PorEdx

d yor kdx

∴ =

+

+

C.F of this diy = A cos kx It is clear at And at x =

....e A∴ =

2 cos

co

e A

y e

=

∴ =

Where be

the deflec

tan

dy edx

or kx

∴ =−

=

nal QuestiThe link ocircular cof the linkand elastcan carryAccording t

crP = σ

cr

.

Hear A=ar

least radiu

For both e

P 40

y A⎡⎢⎢⎢⎣

∴ =

nal QuestiFind the ssection 60

ance 'x' from

2

.

0

0

P y

P yEI

y

−

=

⎡⎢= ⎢⎢⎣∵

ifferential e+ B sin kx, Wx = 0, y = e , y= 2e

..............( )i

s sin

2oss

k B k

ekx

+

⎡ −⎢+⎢⎣

ending mom

tion will be

sin

2 cossin

ek kx k

kk

+

−=

ion ESE-1of a mechacross-sectiok are hingic modulus

y. Use Johnto Johnson's

σπ21

4

rea of cross

us of gyratio

end hinged

0 63.62 1

y

n E

⎡ ⎛⎜− ⎜⎜⎝⎣

×⎡⎢⎢⎢⎣

ion GATE-shortest le00 mm × 10

Theoriem end A defl

Pk giEI

=∵

quation Where A & B

cos ssin

k or

e kk

⎤− ⎥⎥⎦

ment is maxi

maximum s

2 cos.sin

e ekk

⎡ −⎢⎢⎣

996 anism is suon with diaged. It is ms = 200 kN

non's equatis equation

π

2

s section=

Ion (k) =A

n=1

k

⎤⎛ ⎞ ⎥⎟⎟ ⎥⎟⎝ ⎠ ⎥⎦

− 2π4 1× ×

-1995 ngth of a h00 mm, for

es of Columlection of th

iven⎤⎥⎥⎥⎦

B constant.

2s

in

eB

kx

⎡ −⎢=⎢⎣

mum,

so 0

s cos

dydx

k kx

=

⎤⎥ =⎥⎦

ubjected toameter 9 m

made of steeN/mm2. Calcion.

2

π

π64πd

2

4

d 63.624

4

40

d

=

⎛ ⎞⎟⎜ ⎟⎜ ⎟⎜ ⎟⎜⎝ ⎠= =

⎛ ⎞⎟⎜ ⎟⎜ ⎟⎜ ⎟⎜⎝ ⎠

3

0(200 10× ×

hinged steer which the

mne

cosine k

k⎤⎥⎥⎦

0=

axial commm and lenel having yculate the

22

2.254

mm

d m= =

2

3

2002.25)⎛ ⎞⎟⎜ ⎟⎜ ⎟⎜⎝ ⎠×

el column he elastic E

mpressive fongth 200 mmyield stren

critical lo

mm

=15.262kN⎤⎥⎥⎥⎦

having a reuler formu

S K Mo

orce. It hasm. The twogth = 400 N

oad that th

N

ectangular ula applies

ondal’s

s solid o ends N/mm2

he link

cross-. Take



yield strength and modulus of elasticity value for steel as 250 MPa and 200 GPa respectively.

Answer: Given: Cross-section, (= b x d) = 600 mm x 100 mm = 0.6 m x 0.1 m = 0.06 m2;

Yield strength = 2 12 2250 250 / ; 200 200 10 /P MPa MN m E GPa N mA= = = = ×

3 35 40.6 0.1Least areamoment of Inertia, 5 10 m

12 12bdI −×

= = = ×

Length of the column, L :

( )

52 4 2

2

5 10, 8.333 100.6 0.1

[ where area of cross-section, radius of gyration ]

IAlso k mA

I AK A k

−−×

= = = ××

= = =∵

2 2

2 2

From Euler's formula for column, we have

, cre

EI EICrushing load PL Lπ π

= =

( )

e2 2

2

2

2

2 22

For bothendhinged type of column, = L

/

cr

cr

cr

L

EAkor PL

P EIor Yield stressA L

Ekor LP A

π

π

π

=

⎛ ⎞⎟⎜ =⎟⎜ ⎟⎟⎜⎝ ⎠

=

Substituting the value,we get

2 92

6

200 10 0.0008333 6.58250 10

2.565

L

L m

π × × ×= =

×=

Conventional Question GATE-1993 Question: Determine the temperature rise necessary to induce buckling in a lm long

circular rod of diameter 40 mm shown in the Figure below. Assume the rod to be pinned at its ends and the coefficient of thermal expansion as 6 020 10 / C−×. Assume uniform heating of the bar.

Answer: Letusassume the buckling load be'P'.



( )

[ ]

2

e2

2

e2

. . , Where is the temperature rise.

..,

where L =equivalent length

. . QL =L For bothendhinged

cre

L L t tLor t

LPL L AEAlso L or PAE L

EIPL

EI L A EorLL

δδ

δδ

π

π δ

= ∝

=∝

= =

= −−−

=

( )

( ) ( )

2

2 2

2

42

0

2 4 6

. . . .Substituting the values,we get

0.04064Temperature rise 49.35

1 0.040 20 104

Ior LLA

L I ItL LA L L A

t C

πδ

δ π π

ππ

π −

=

= = =∝ ∝ ∝

× ×= =

× × × ×

So the rod will buckle when the temperature rises more than 49.35°C.


14. Strain Energy Method

Theory at a Glance (for IES, GATE, PSU) 1. Resilience (U)

• Resilience is an ability of a material to absorb energy when

elastically deformed and to return it when unloaded.

• The strain energy stored in a specimen when stained within

the elastic limit is known as resilience.

2σU = U =2 2

∈× ×2 EV o lu m e o r V o lu m eE

2. Proof Resilience • Maximum strain energy stored at elastic limit. i.e. the strain energy stored in the body upto

elastic limit.

• This is the property of the material that enables it to resist shock and impact by storing energy. The measure of proof resilience is the strain energy absorbed per unit volume.

3. Modulus of Resilience (u) The proof resilience per unit volume is known as modulus of resilience. If σ is the stress due to

gradually applied load, then

2σu = u =2 2

∈2 Eo rE

4. Application

2 22

22

3P .4 4= π π2 2 (2 ) 2.4 4

LL PP LUdAE d E E

= +

Strain energy becomes smaller & smaller as the cross sectional area of baris increased over more & more of its length i.e. A , U↑ ↓

5. Toughness • This is the property which enables a material to be twisted, bent or stretched under impact

load or high stress before rupture. It may be considered to be the ability of the material to

LL/4

2d

P


C

M

6

Chapter-14 absor

absor

• Toug

• The a

• Toug

• The

struc

Modulus of• The

to ab

• The

that

witho

• The a

diagr

which

be a

mate

fractu

6. Strain e

Strain e•

su

• Total

• Case

•Sol

Ho•

rb energy i

rbed after be

ghness is an

ability to wit

ghness = stre

materials w

ctures that w

f Toughnesability of un

sorb energy

amount of

the mat

out failure.

area under

ram is called

h is a meas

absorbed by

erial due to i

ures.

energy in

2

energy per u

τ or, 2

=s G

l Strain Ene

12

=

⎛∴ = ⎜

⎝

s

s

U

U

or =sU

es

, slid shaft U

,llowshaft

in the plast

eing stressed

ability to ab

thstand occa

ength + duct

with higher

will be expos

ss nit volume

y in the plast

work per u

erial can

the entire s

d modulus of

sure of ener

y the unit

impact loadi

shear an

2

s

unit volume

u2γ= G

ergy (U) for a

2

12

φ=

⎞⎟⎠

T

T L orGJ

2max

2

τ 22

π= ∫L

G r

2maxτ

4π= × r

G2maxτ

4sUG

= ×

Strain Entic zone. Th

d upto the p

bsorb energy

asional stres

tility

r modulus

sed to sudde

of material

tic range.

unit volume

withstand

tress strain

f toughness,

gy that can

volume of

ing before it

nd torsion

se, (u )

a Shaft in T

21 GJ2

φL

2ρ ρ∫ d

2r L

( 4 4

2

D dD

π −×

nergy Methhe measure

point of fract

y in the plas

sses above th

of toughne

n and impac

l

e

d

n

n

f

t

n

orsion

)4 2maxτ

4L

G= ×

hode of toughne

ture.

stic range.

he yield stre

ess are use

ct loads.

UT

( )2 2

2

D dD+

×

O

T

ess is the

ess without f

ed to make

T = σu εf

Volume×

A

Bdφ

S K Moamount of

fracture.

e componen

ondal’s energy

ts and

φ


Chapter-

•T

w

•

•

•

7. Strai

• An

• St

o r U

• C

• Im

8. Casti

-14

s = Le

Thin walled

where

Conical sp

Cantilever b

Helical spr

n energy

ngle subtend

train energy

=

=

∫

∫

0

0

U2

2

L

b

L

b

ME

E IU

ases

o Canti

o Simpl

mportant N

o For pu

•

•

•

o For no

•

•

iglione’s

,

ength of me

=sd tube U

S, U

=pring

beam with l

, =sring U

in bendi

ded by arc,

y stored in b

⎛ ⎞⎜ ⎟⎝ ⎠∫

2

22

20

.x

L

M d xE I

d yd x

lever beam

ly supported

Note

ure bending

M is const

MLEI

θ =

=2

2M LU

EIon-uniform b

Strain en

Strain en

theorem

Strain2τ

4ean centre lin

= × sLtG

2

2π23

0

2

P=2GJ

φ⎛ ⎞⎜ ⎟⎝ ⎠∫

∫n

GJ ddx

R

load 'p' at en

2 3πP R nGJ

ng.

θ .= ∫ xM dxEI

eam.

d x

with a end l

d with a load

g

tant along th

if Misknow

bending

ergy in shea

ergy in bend

n Energy M

ne

2 2

3

2

( var

π

α

⎞ =⎟⎠ ∫

GJdx

d R

s3nd, U5⎛

= ⎜⎝

( 2π=∵L

x

⎛⎜⎝∵

2

2 d yd x

load P , bU

d P at centre

he length ‘L

θ=2

wn2

EI ifL

ar is neglecte

ding is only

Method

2

0

.

ries with )

π ⎛ ⎞⎜ ⎟⎝ ⎠

∝

∫n PR R

GJ

2 ⎞⎟⎠

P LbhG

)πRn

⎞= − ⎟

⎠

ME I

2 3

6=b

P LEI

e, 2

96=b

P LUE

L’

θcurvature

ed

considered.

. (

)

α =R d R R

3LEI

θ / isknowL

S K

)Radius

n

Mondal’s


Chapter-14 Strain Energy Method S K Mondal’s

δ∂ =∂ n

n

UP

1 ⎛ ⎞∂∂ = ⎜ ⎟∂ ∂⎝ ⎠∫ x

xMU M dx

p EI p

• Note:

o Strain energy, stored due to direct stress in 3 coordinates

21 (σ ) 2 σ σ2

μ⎡ ⎤= −⎣ ⎦∑ ∑x x yUE

o = =If σ σ σ ,in case of equal stress in 3 direction thenx y z

2 23σ σU= [1 2μ] (volume strain energy)

2 2E k− =


Chapter-

OBJ

StrainGATE-1.

GATE-2.

GATE-2(

GATE-3.

GATE-4.

-14

JECTIV

Prev

n EnergThe strashown in

(a) 2 3

3P L

EI

3

3PLEI

is th

of elastic

2 3

( )3P La

EI

i). 1U and Uforces 1Pcombine(a) U U=(c) 1U U<

The strmaterialresiliencare respe(a) 28 × 10(b) 28 × 10(c) 14 × 10(d) 76 × 1

A squaresame barratio of tin the fir(a) 16

VE QU

vious

gy or Rain energy n the figure

(b

he deflecti

city, E, mom

( )b

2U are the s

2and P , resd action of

1 2U U+

1 2U+

ress-strain l is showce and touectively 04, 76 × 104

04, 48 × 104

04, 90 × 104

04

e bar of sidr is then usthe strain rst case, is:

Strain

UESTI

20-Ye

Resilienstored in

e is:

b) 2 32

3P LEI

on under t

ment of ine

2 3

)6P L

EI

train energspectively.f 1 2P and P w

behaviouwn in figughness, in

de 4 cm andsed as a caenergies, s

(b) 40

n Energy M

IONS

ears G

nce the beam

the load P

ertia-I]. The

( )4Pc

E

gies stored The strainwill be

(b (d

ur of a gure. Its n Nm/m3,

d length 10antilever bestored in th

00

Method

(GAT

GATE Q

with flexu

(c) 43

of a cantile

e strain en

2 3LEI

d in a prismn energy U

b) 1 2U U U=d) 1U U U> +

0 cm is subeam and suhe bar in t

(c) 10

TE, I

Questi

ural rigidity

2 3

3P LEI

ever beam

nergy due to

2

( )48P Ld

E

matic bar dstored in t

[C

2U

bjected to aubjected tothe second

00

S K

ES, I

ions

y EI and l[GA

(d) 8

[length L,

o bending [GA

3LEI

due to axiathe same bCE: GATE-2

[GA

an axial loa all end loacase to th

[GA(d) 25

Mondal’s

IAS)

oaded as ATE-2008]

2 383P LEI

modulus

is: ATE-1993]

al tensile ar due to 2007]

ATE-2000]

ad P. The ad P. The at stored

ATE-1998]500



GATE-4(i) For linear elastic systems, the type of displacement function for the strain energy is

(a) linear (b) quadratic [CE: GATE-2004] (c) cubic (d) quartic GATE-4(ii)A mild steel specimen is under uniaxial tensile stress. Young’s modulus and

yield stress for mild steel are 52 10× MPa and 250 MPa respectively. The maximum amount of strain energy per unit volume that can be stored in this specimen without permanent set is

(a) 3156 Nmm/ mm (b) 315.6 Nmm/ mm [CE: GATE-2008]

(c) 31.56 Nmm/ mm (d) 30.156 Nmm/ mm

Toughness GATE-5. The total area under the stress-strain curve of a mild steel specimen tested up

to failure under tension is a measure of [GATE-2002] (a) Ductility (b) Ultimate strength (c) Stiffness (d) Toughness GATE-6. For a ductile material, toughness is a measure of [GATE-2013]

(a) resistance to scratching (b) ability to absorb energy up to fracture (c) ability to absorb energy till elastic limit (d) resistance to indentation


Strain Energy or Resilience IES-1. What is the strain energy stored in a body of volume V with stress σ due to

gradually applied load? [IES-2006]

(a) E

Vσ

(b) 2E

Vσ

(c) 2V

Eσ

(d) 2

2VE

σ

Where, E = Modulus of elasticity IES-1(i). A circular bar L m long and d m in diameter is subjected to tensile force of F

kN. Then the strain energy, U will be (where, E is the modulus of elasticity in kN/m2 ) [IES-2012] 4 ∙ ∙ 2 ∙ 3 ∙

IES-1(ii). Statement (I): Ductile materials generally absorb more impact energy than the

brittle materials. Statement (II): Ductile materials generally have higher ultimate strength than brittle materials. [IES-2012] (a) Both Statement (I) and Statement (II) are individually true and Statement (II) is the correct explanation of Statement (I) (b) Both Statement (I) and Statement (II) are individually true but Statement (II) is not the correct explanation of Statement (I) (c) Statement (I) is true but Statement (II) is false (d) Statement (I) is false but Statement (II) is true

IES-2. A bar having length L and uniform cross-section with area A is subjected to

both tensile force P and torque T. If G is the shear modulus and E is the Young's modulus, the internal strain energy stored in the bar is: [IES-2003]

(a) 2 2

2T L P LGJ AE

+ (b) 2 2

2T L P LGJ AE

+ (c) 2 2

2 2T L P LGJ AE

+ (d) 2 2T L P L

GJ AE+



IES-3. Strain energy stored in a body of volume V subjected to uniform stress s is:

[IES-2002] (a) s E / V (b) sE2/ V (c) sV2/E (d) s2V/2E IES-4. A bar of length L and of uniform cross-sectional area A and second moment of

area ‘I’ is subjected to a pull P. If Young's modulus of elasticity of the bar material is E, the expression for strain energy stored in the bar will be:

[IES-1999]

2 2 2 2P L PL PL P L(a) (b) (c) (d)

2AE 2EI AE AE

IES-5. Which one of the following gives the correct expression for strain energy

stored in a beam of length L and of uniform cross-section having moment of inertia ‘I’ and subjected to constant bending moment M? [IES-1997]

( ) ( ) ( ) ( )2 2

a b c d 2 2

ML ML M L M LEI EI EI EI

IES-6. A steel specimen 150 2mm in cross-section stretches by 0·05 mm over a 50 mm

gauge length under an axial load of 30 kN. What is the strain energy stored in the specimen? (Take E = 200 GPa) [IES-2009]

(a) 0.75 N-m (b) 1.00 N-m (c) 1.50 N-m (d) 3.00 N-m IES-7. What is the expression for the strain energy due to bending of a cantilever

beam (length L. modulus of elasticity E and moment of inertia I)? [IES-2009]

(a) 2 3

3P L

EI (b)

2 3

6P L

EI (c)

2 3

4P L

EI (d)

2 3

48P L

EI

IES-8. The property by which an amount of energy is absorbed by a material without

plastic deformation, is called: [IES-2000] (a) Toughness (b) Impact strength (c) Ductility (d) Resilience IES-8a Resilience of material becomes important when it is subjected to :

(a) Fatigue (b) Thermal stresses (c) Shock loading (d) Pure static loading [IES-2011]

IES-9. 30 C 8 steel has its yield strength of 400 N/mm2 and modulus of elasticity of 2 ×

105 MPa. Assuming the material to obey Hooke's law up to yielding, what is its proof resilience? [IES-2006]

(a) 0·8 N/mm2 (b) 0.4 N/mm2 (c) 0·6 N/mm2 (d) 0·7 N/mm2 IES9a Match List I with List II and select the correct answer using the code given

below the lists: [IES-2010] List I List II

A. Point of inflection 1. Strain energy B. Shearing strain 2. Equation of bending C. Section modulus 3. Equation of torsion D. Modulus of resilience 4. Bending moment diagram


Toughness IES-10. Toughness for mild steel under uni-axial tensile loading is given by the shaded

portion of the stress-strain diagram as shown in [IES-2003]




Strain Energy or Resilience IAS-1. Total strain energy stored in a simply supported beam of span, 'L' and flexural

rigidity 'EI 'subjected to a concentrated load 'W' at the centre is equal to: [IAS-1995]

(a) 2 3

40W L

EI (b)

2 3

60W L

EI (c)

2 3

96W L

EI (d)

2 3

240W L

EI

IAS-2. If the cross-section of a member is subjected to a uniform shear stress of

intensity 'q' then the strain energy stored per unit volume is equal to (G = modulus of rigidity). [IAS-1994]

(a) 2q2/G (b) 2G / q2 (c) q2 /2G (d) G/2 q2 IAS-4. Which one of the following statements is correct? [IAS-2004] The work done in stretching an elastic string varies (a) As the square of the extension (b) As the square root of the extension (c) Linearly with the extension (d) As the cube root of the extension

Toughness IAS-5. Match List-I with List-II and select the correct answer using the codes given

below the lists: [IAS-1996] List-I (Mechanical properties) List-II (Meaning of properties) A. Ductility 1. Resistance to indentation B. Hardness 2. Ability to absorb energy during plastic C. Malleability deformation D. Toughness 3. Percentage of elongation 4. Ability to be rolled into flat product Codes: A B C D A B C D (a) 1 4 3 2 (b) 3 2 4 1 (c) 2 3 4 1 (d) 3 1 4 2 IAS-6. Match List-I (Material properties) with List-II (Technical

definition/requirement) and select the correct answer using the codes below the lists: [IAS-1999]

List-I List-II A. Hardness 1. Percentage of elongation



B. Toughness 2. Resistance to indentation C. Malleability 3. Ability to absorb energy during plastic deformation D. Ductility 4. Ability to be rolled into plates Codes: A B C D A B C D (a) 3 2 1 4 (b) 2 3 4 1 (c) 2 4 3 1 (d) 1 3 4 2 IAS-7. A truck weighing 150 kN and travelling at 2m/sec impacts which a buffer

spring which compresses 1.25cm per 10 kN. The maximum compression of the spring is: [IAS-1995]

(a) 20.00 cm (b) 22.85 cm (c) 27.66 cm (d) 30.00 cm



OBJECTIVE ANSWERS

GATE-1. Ans. (B) 4 3 42 2 2 2

0 0 32 2 2 2

L L L L

L L

M dx M dx M dx M dxEI EI EI EI

= + +∫ ∫ ∫ ∫

3 42 2 2 2

0 0 3

32 2 2 3

0

2 By symmetry2 2 2 2

( ) ( ) 222 2 3

L L L L

L L

L L

L

M dx M dx M dx M dxEI EI EI EI

Px dx PL dx P LEI EI EI

⎡ ⎤⎢ ⎥= + =⎢ ⎥⎢ ⎥⎣ ⎦

= + =

∫ ∫ ∫ ∫

∫ ∫

GATE-2. Ans. (b) We may do it taking average

Strain energy = Average force x displacement = 3

2 3⎛ ⎞× =⎜ ⎟⎝ ⎠

P PLEI

2 3

6P L

EI

Alternative method: In a funny way you may use Castiglione’s theorem, UP

δ∂

=∂

. Then

UP

δ∂

=∂

3

3PLEI

= or 3

3PLU U PEI

= ∂ = ∂∫ ∫ Partially integrating with respect to P we get

2 3P LU6EI

=

GATE-2(i). Ans. (d)

We know that Strain Energy, =2P LU

2AE

It is obvious from the above equation that strain energy is proportional to the square of load applied. We know that sum of squares of two numbers is less than the square of their sum. Thus > +1 2U U U .

GATE-3. Ans. (c) Resilience = area under this curve up to 0.004 strain

= 6 41 0.004 70 10 14 102× × × = × Nm/m3

Toughness = area under this curve up to 0.012 strain

= ( ) ( ) ( )4 6 6114 10 70 10 0.012 0.004 0.012 0.004 120 70 102

× + × × − + × − × − × Nm/m3

490 10= × Nm/m3

GATE-4. Ans. (d)

⎛ ⎞⎜ ⎟⎝ ⎠= =

2

2

1

W ALW LAU

2E 2AE

= = =⎛ ⎞⎜ ⎟⎝ ⎠

⎛ ⎞= = × =⎜ ⎟⎝ ⎠

2 3 2 3 2 3

2 44

222

21

W L W L 2W LU16EI Ea6E a

12

U 4L 100or 4 2500U 4a

GATE-4(i) Ans. (b)

Strain Energy = × σ × ε = ε21 1 E2 2

GATE-4(ii)Ans. (d) The strain energy per unit volume may be given as

σ

= × = × = −×

2 23

51 1 (250) 0.156 N mm/ mm2 E 2 2 10

yu

GATE-5. Ans. (d)



GATE-6. Ans. (b)

IES

IES-1. Ans. (d) Strain Energy =21 . V

2 Eσ ×

IES-1(i). Ans. (c) IES-1(ii). Ans. (c)

IES-2. Ans. (c) 1 1 1 1Internal strain energy = P + P +2 2 2 2

PL TLT TAE GJ

δ θ =

IES-3. Ans. (d)

IES-4. Ans. (a) ( )21 1Strain energy x stress x strain x volume = .

2 2 2P P L PLALA A E AE

⎛ ⎞ ⎛ ⎞= × × × =⎜ ⎟ ⎜ ⎟⎝ ⎠ ⎝ ⎠

IES-5. Ans. (d) IES-6. Ans. (a) Strain Energy stored in the specimen

( ) −

−

× ×⎛ ⎞= δ = = = =⎜ ⎟ × × × ×⎝ ⎠

2 32

6 9

30000 50 101 1 PL P LP P 0.75 N-m2 2 AE 2AE 2 150 10 200 10

IES-7. Ans. (b) Strain Energy Stored ⎛ ⎞

= = =⎜ ⎟⎝ ⎠

∫LL 2 2 3 2 3

0 0

(Px) dx P x P L2E 2EI 3 6EI

IES-8. Ans. (d) IES-8a. Ans. (c)

IES-9. Ans. (b) Proof resilience ( ) ( )222

p 5

4001 1R . 0.4N / mm2 E 2 2 10

σ= = × =×

IES9a Ans. (b) IES-10. Ans. (d) Toughness of material is the total area under stress-strain curve.

IAS

IAS-1. Ans. (c) Strain energy = 2L L/2 L/22 2 2 3

0 0 0

M dx M dx 1 Wx W L2 dx2EI 2EI EI 2 96EI

⎛ ⎞= × = × =⎜ ⎟⎝ ⎠∫ ∫ ∫

Alternative method: In a funny way you may use Castiglione’s theorem, U UP W

δ∂ ∂

= =∂ ∂

We know that 3

48WL

EIδ = for simply supported beam in concentrated load at mid span.

Then U UP W

δ∂ ∂

= =∂ ∂

3

48WL

EI= or

3

48WLU U W

EI= ∂ = ∂∫ ∫ partially integrating with

respect to W we get 2 3W LU

96EI=

IAS-2. Ans. (c)

IAS-4. Ans. (a) ( )22

22

1 12 2 2

lE E

E Lδσ ⎡ ⎤

⎢ ⎥= ∈ = ⎢ ⎥⎢ ⎥⎣ ⎦

IAS-5. Ans. (d) IAS-6. Ans. (b) IAS-7. Ans. (c) Kinetic energy of the truck = strain energy of the spring



32

22 2

150 10 29.811 1 mvmv kx or x 0.2766m 27.66cm10 10002 2 k

0.0125

⎛ ⎞× ×⎜ ⎟⎝ ⎠= = = = =

×⎡ ⎤⎢ ⎥⎣ ⎦


Conventional Question IES 2009 Q. A close coiled helical spring made of wire diameter d has mean coil radius R,

number of turns n and modulus of rigidity G. The spring is subjected to an axial compression W.

(1) Write the expression for the stiffness of the spring. (2) What is the magnitude of the maximum shear stress induced in the spring

wire neglecting the curvature effect? [2 Marks]

Ans. (1) Spring stiffness, K =

(2) Maximum shear stress,

Conventional Question IES 2010 Q. A semicircular steel ring of mean radius 300 mm is suspended vertically with

the top end fixed as shown in the above figure and carries a vertical load of 200 N at the lowest point. Calculate the vertical deflection of the lower end if the ring is of rectangular cross- section 20 mm thick and 30 mm wide.

Value of Elastic modulus is 5 22 10 N/mm× . Influence of circumferential and shearing forces may be neglected. [10 Marks]

Ans. Load applied, F = 200 N Mean Radius, R = 300 mm Elastic modules, E = 5 22 10 N/mm× I = Inertia of moment of cross – section

3bdI b = 20 mm

12=

( )3 4

d = 30 mm

20 30= = 45,000 mm

12×

⇒ Influence of circumferential and shearing force are neglected strain energy at the section.

4

3W GdX 8nD

=

38WD

dτ =

π



( )

2

0

2 2 2

022

5

3

M Rd Ru = for 102EI 4

M = F RsinM = R sinF

u FR sin FR = = d F EI 2EI

200 300FR = = 2EI 2 2 10 45000

3.14 10 mm.

π

π

−

θ ≥

× θ∂

⇒ θ∂

∂ θδ θ ⇒ × π∂

π× ×πδ× × ×

δ = ×

∫

∫

Conventional Question GATE-1996 Question: A simply supported beam is subjected to a single force P at a distance b from

one of the supports. Obtain the expression for the deflection under the load using Castigliano's theorem. How do you calculate deflection at the mid-point of the beam?

Answer: Let load P acts at a distance b from the support B, and L be the total length of the beam.

Re , ,

Re ,

A

B

Pbaction at A R andL

Paaction at A RL

=

=

Strain energy stored by beam AB, U = Strain energy stored by AC (U AC) + strain energy stored by BC (U BC)

( ) ( ) ( )

( ) ( )

2 2 2 2 3 2 2 3

2 20 0

22 22 2 2 2 2 2

2

2 22 2

. .2 2 6 6

)6 66

2Deflection under the load ,

6 3

a bPb dx Pa dx P b a P b ax xL EI L EI EIL EIL

P L b bP b a P b aa b a b LEIL EILEIL

P L b b P L b bUP yP EIL EIL

δ

⎛ ⎞ ⎛ ⎞= + = +⎜ ⎟ ⎜ ⎟⎝ ⎠ ⎝ ⎠

−⎡ ⎤= + = = + =⎣ ⎦

− −∂= = = =∂

∫ ∫

∵

Deflection at the mid-span of the beam can be found by Macaulay's method. By Macaulay's method, deflection at any section is given by



( ) ( )

( ) ( )( ) ( )

( )

332 2

3

32 2

32 22

2 2 2

6 6 6Where y is deflection at any distance x from the support.

At , , . at mid-span,2

/ 2 26 6 2 6

2or,

48 12 48

448

P x aPbx PbEIy L b xL L

Lx i e

LP aPb L Pb LEIy L bL L

Pb L b P L aPbLEIy

Py bL b L b LEI

−= − − −

=

⎛ ⎞−⎜ ⎟× ⎝ ⎠= − − × −

− −= − −

= − − − −( )32a⎡ ⎤⎣ ⎦


15. Theories of Failure

Theory at a Glance (for IES, GATE, PSU) 1. Introduction

• Failure: Every material has certain strength, expressed in terms of stress or strain, beyond

which it fractures or fails to carry the load.

• Failure Criterion: A criterion used to hypothesize the failure.

• Failure Theory: A Theory behind a failure criterion.

Why Need Failure Theories?

• To design structural components and calculate margin of safety.

• To guide in materials development.

• To determine weak and strong directions.

Failure Mode

• Yielding: a process of global permanent plastic deformation. Change in the geometry of the

object.

• Low stiffness: excessive elastic deflection.

• Fracture: a process in which cracks grow to the extent that the component breaks apart.

• Buckling: the loss of stable equilibrium. Compressive loading can lead to bucking in

columns.

• Creep: a high-temperature effect. Load carrying capacity drops.

Failure Modes: Excessive elastic deformation

Yielding Fracture

1. Stretch, twist, or bending

2. Buckling 3. Vibration

• Plastic deformation at room temperature

• Creep at elevated temperatures

• Yield stress is the important design factor

• Sudden fracture of brittle materials

• Fatigue (progressive fracture)

• Stress rupture at elevated temperatures

• Ultimate stress is the important design factor

2. Maximum Principal Stress Theory (W. Rankin’s Theory- 1850) – Brittle Material The maximum principal stress criterion:


Chapter-

• Ra

la

th

• Cr

pr

• Cr

sa

• Th

be

• U

• Li

• G

3. Maxi(Guest’The Tres

• Al

• Yi

si

-15 ankin stated

argest princi

he onset of fr

rack will st

rincipal stre

riterion has

ame in comp

Failu

his theory o

een used suc

sed to descr

imitations

o Doesn

o Doesn

mater

eneralizatio

mum Shes or Tres

sca Criterio

lso known a

ielding will

mple tension

d max princ

ipal stress e

racture, |σ1

tart at the

ess at that po

s good exper

pression and

ure surface

of yielding h

ccessfully for

ribe fracture

n’t distinguis

n’t depend o

rials

on to 3-D str

ear Stresssca’s Theon:

s the Maxim

occur when

n test.

Theoipal stress t

xceeds the u

| = σu OR |σ

most highly

oint reaches

rimental ver

d tension

according

has very poo

r brittle mat

of brittle m

sh between

on orientati

ess case is e

s or Stresory-1868

mum Shear S

the maximu

ories of Fatheory as fol

ultimate str

σ3| = σu

y stressed p

s σu

rification, e

g to maximu

or agreemen

terials.

materials su

tension or co

ion of princ

easy:

ss differe)- Ductile

Stress criter

um shear st

ailurellows- a mat

rength σu in

point in a b

ven though

um princip

nt with expe

uch as cast i

ompression

cipal planes

ence theoe Material

rion.

tress reache

terial fails by

a simple te

rittle mater

it assumes

pal stress th

riment. How

iron

s so only ap

ory

s that which

S K y fracturing

nsion test. T

rial when th

s ultimate s

heory

wever, the t

pplicable to

h caused yie

Mondal’s g when the

That is, at

he largest

trength is

theory has

o isotropic

elding in a


C

4T

T

e

th

e

U

σ

σ

5

V

Chapter-15 • Reca

princ

maxi

If 1σ

• Failu

stres

• This

4. Strain EThe theory

This theory i

nergy absor

he stress sy

nergy at the

21

12

UE

σ⎡= ⎣

2 2 21 2 3σ σ σ+ +2 21 2 2σ σ μ+ −

5. Shear STheory

Von-Mises C• Also • Base

ll that yield

cipal stresse

imum shear

2 3σ σ> > T

ure by slip (

s fτ as deter

theory gives

Failur

Energy Thassociated

is based on

rbed by the m

stem causin

e elastic limi

2 22 3σ σ+ + −

(23 1 22μ σ σ−

21 2 yμσ σ σ=

Strain Eny or Von-MCriterion: known as thd on a more

ding of a m

es. This sho

stress in th

Then 1σ σ−

(yielding) oc

rmined in a

s satisfactory

re surface a

heory (Had with Haig

the assump

material at f

ng it. The str

it in simple

( 1 22μ σ σ σ+

2 3 3σ σ σ+ +

For 2

nergy TheMisses T

he Maximum complex vie

Theoriematerial occu

ould indicate

e material r

3 yσ σ=

ccurs when t

uniaxial ten

ry result for

according t

aigh’s Thgh

ption that st

failure up to

rain energy

tension.

2 3 3 1σ σ σ σ+

) 23 1 yσ σ=

2D- stress

eory (Distheory)-Du

m Energy of ew of the rol

es of Failuurred by slip

e to you tha

rather than t

the maximu

nsion test.

ductile ma

to maximu

eory)

trains are re

o this point

per unit vol

)2

1 2y

Eσ

⎤ =⎦

For 3

tortion Enuctile Ma

Distortion cle of the prin

reppage betwe

at yielding

the maximu

um shearing

aterial.

um shear st

ecoverable u

is a single v

lume causin

3D- stress

nergy Theaterial

criterion ncipal stress

een planes

of a materi

um normal s

g stress, maτ

tress theory

up to the ela

valued funct

ng failure is

eory or M

s differences

S K Mooriented at

al depends

tress.

x exceeds th

y

astic limit, a

ion indepen

equal to the

Mises-Hen

s.

ondal’s 45° to

on the

he yield

and the

ndent of

e strain

nky


Chapter-

• Inco

• W

• Fo

• It

• Insoan

• Ththon

• It

6. MaxiAccording

strain at

and minim

-15 n simple termontributing t

When the crit

or a state of

21σ −

is often con

eσ =

eorσ

n formulatino the theorynisotropic mhe von Misehere is little n or between

gives very g

mum Pring to this the

the tensile

mum princip

ms, the von to the charaterion is app

f plane stres

1 2 2σ σ σ− +

nvenient to e

1 21 (2

σ σ⎡ −⎢⎣

1 (2 xσ⎡= −⎢⎣

ng this failury given is

materials. es theory is difference i

n these two tgood result i

ncipal Streory, yieldin

yield point

pal strains c

TheoMises critercterization o

plied, its rela

s ( 3σ =0)

2 22 yσ=

express this

22 2) (σ σ+ −

2) (y yσ σ− +

re theory weonly applic

a little lessin their predtheories. in ductile m

rain Theong will occur

in either sim

correspondin

ories of Farion considerof yield onseationship to

as an equiv

23 3) (σ σ+ −

2) (z xσ σ− +

e used genecable to tho

s conservativdictions of fa

material.

ory (St. Ver when the

mple tension

ng to σ1 and

ailurers the diameet in isotropithe uniaxia

alent stress1/22

1)σ ⎤⎥⎦

2) 6x zσ− +

ralized Hooose materia

ve than the ailure. Most

enant Themaximum

n or compre

σ2, in the lim

eters of all tic materials

al tensile yie

, σ e:

2 26( xy yzτ τ+ +

ke's law for ls but it ca

Tresca theot experiment

eory) principal st

ession. If ε1

miting case

S K three Mohr’s. ld strength

1/22 )zxτ ⎤+ ⎥⎦

an isotropican be gene

ory but in mtal results te

train just ex

and ε2 are

Mondal’s s circles as

is:

c material ralized to

most cases end to fall

xceeds the

maximum


C

7

M

H

c

8A

s

Chapter-15

7. Mohr’s

Mohr’s Theo

• Mohr

tensi

• In M

repre

plane

• Point

minim

• Expe

failur

simp

enve

• Mohr

Higher shear

ompression

8. CompaA comparison

hown in figu

theory- B

ory

r’s theory is

ion and comp

Mohr’s circle

esents states

e is the one w

ts on the o

mum princip

eriments are

re. Each sta

le compress

elope (AB &

r’s envelope

r stresses ar

rison n among the

ure

Brittle Ma

s used to pr

pression. Cr

e, we note

s of stress o

with maxim

outer circle

pal stresses

e done on a

ate defines

ion, and pur

A’B’)

thus repres

re to the lef

e different f

Theorie

aterial

redict the fr

riterion mak

that τ dep

n planes wi

mum τ , poin

are the we

are sufficien

given mate

a Mohr’s ci

re shear, th

ents the locu

ft of origin,

failure theor

es of Failu

fracture of a

kes use of Mo

ends on σ,

ith same σ b

nt P.

eakest plan

nt to decide

erial to dete

ircle. If the

e three resu

us of all pos

since most

ries can be m

re

a material h

ohr’s circle

or τ = f(σ

but differing

es. On thes

whether or

ermine the

e data are o

ulting circles

sible failure

brittle mate

made by sup

having diffe

σ). Note the

g τ , which m

se planes th

not failure w

states of str

obtained fro

s are adequa

e states.

erials have

perposing th

S K Mo

erent proper

e vertical li

means the w

he maximu

will occur.

ress that re

om simple t

ate to constr

higher stren

he yield surfa

ondal’s

rties in

ine PC

weakest

um and

esult in

ension,

ruct an

ngth in

faces as


Chapter-

-15

Theoories of Faailure S K Mondal’s


Chapter-15 Theories of Failure S K Mondal’s



Maximum Shear stress or Stress Difference Theory GATE-1. Match 4 correct pairs between list I and List II for the questions [GATE-1994] List-I List-II (a) Hooke's law 1. Planetary motion (b) St. Venant's law 2. Conservation Energy (c) Kepler's laws 3. Elasticity (d) Tresca's criterion 4. Plasticity (e) Coulomb's laws 5. Fracture (f) Griffith's law 6. Inertia GATE-2. Which theory of failure will you use for aluminium components under steady

loading? [GATE-1999] (a) Principal stress theory (b) Principal strain theory (c) Strain energy theory (d) Maximum shear stress theory GATE-2(i) An axially loaded bar is subjected to a normal stress of 173 MPa. The shear

stress in the bar is [CE: GATE-2007] (a) 75 MPa (b) 86.5 MPa (c) 100 MPa (d) 122.3 MPa

Shear Strain Energy Theory (Distortion energy theory) GATE-3. According to Von-Mises' distortion energy theory, the distortion energy under

three dimensional stress state is represented by [GATE-2006]

GATE-4. A small element at the critical section of a component is in a bi-axial state of

stress with the two principal stresses being 360 MPa and 140 MPa. The maximum working stress according to Distortion Energy Theory is:

[GATE-1997] (a) 220 MPa (b) 110 MPa (c) 314 MPa (d) 330 MPa GATE-5. The homogeneous state of stress for a metal part undergoing plastic

deformation is 10 5 05 20 00 0 10

T⎛ ⎞⎜ ⎟= ⎜ ⎟⎜ ⎟−⎝ ⎠



where the stress component values are in MPa. Using von Mises yield criterion, the value of estimated shear yield stress, in MPa is (a) 9.50 (b) 16.07 (c) 28.52 (d) 49.41 [GATE-2012]

GATE-6. Match the following criteria of material failure, under biaxial stresses 1σ and

2σ and yield stress ,yσ with their corresponding graphic representations: [GATE-2011]

P. Maximum-normal-stress criterion L.

Q. Minimum-distortion-energy criterion M.

R. Maximum shear-stress criterion N.

(a) P – M, Q – L, R – N (b) P – N, Q – M, R – L (c) P – M, Q – N, R – L (d) P – N, Q – L, R – M


Maximum Principal Stress Theory IES-1. Match List-I (Theory of Failure) with List-II (Predicted Ratio of Shear Stress to

Direct Stress at Yield Condition for Steel Specimen) and select the correct answer using the code given below the Lists: [IES-2006]

List-I List-II A. Maximum shear stress theory 1. 1·0 B. Maximum distortion energy theory 2. 0·577 C. Maximum principal stress theory 3. 0·62 D. Maximum principal strain theory 4. 0·50 Codes: A B C D A B C D (a) 1 2 4 3 (b) 4 3 1 2 (c) 1 3 4 2 (d) 4 2 1 3

σ2σy

–σy

–σy

σyσ1

σ2σy

–σy

–σy

σyσ1

σ2σy

–σy

–σy

σyσ1


C

I

I

I

I I

MI

I

I

I

Chapter-15 ES-2. F

at(a

ES-3. Attt

(

ES-4. Ao(a(b(c(d

ES-5. D(a

ES-5a AcRs(a(b(c(d

MaximuES-6. W

o

ES-7. Ams

(a

ES-8. Pamt(a

ES-9. ABis(a

From a tena factor of she permissa) 50 N/mm2

A circular wisting moheory, theheory, the

( ) 1a 5

A transmissof a) Maximumb) Maximumc) Maximumd) Fatigue s

Design of sha) Guest's th

Assertion (ompressive

Reason (R):trength. a) Both A anb) Both A anc) A is true bd) A is false

um SheWhich one oor Tresca cr

According tmoment in same shaft

a) T/2

Permissibleaccording maximum she same sha) 1/2 M

A rod havinBased on ths 200 MPa, a) 10 kN

sion test, tsafety of 2 sible stress2 (b

solid shafoment of 3

e direct stshear stre

( )b

sion shaft

m normal strm shear strem normal str

trength

hafts madeheory (b) R

(A): A castload. : Shear stren

nd R are indnd R are indbut R is falsbut R is tru

ear strof the folloriterion?

to the maxa circular

as per the

e bending to maxim

shear streshaft is:

ng cross-sehe Tresca f

the failure

Theoriethe yield stand apply

s in the steeb) 57.7 N/mm

ft is subjec300 kNm. Otress is σ ss is τ . The

) 3 9

subjected t

ress theory ss theory

ress and max

e of brittle mRankine’s the

t iron speci

ngth of cast

dividually trudividually true

ue

ress or owing figur

ximum shear shaft is maximum

(b) T

moment imum princ

ss theory o

(b) M

ectional arfailure critee load is:

(b) 20 kN

es of Failutrength of ing maximel shaft subm2

cted to a bOn the basand accore ratio σ/ τ

( ) 9c 5

to bending

ximum shea

materials ieory (c) St

imen shall

iron in com

ue and R is ue but R is N

Stressres represe

ar stress th'T'. The peprincipal s

in a circucipal stresof failure,

rea 100 x 1erion, if th

N

resteel is fou

mum principbjected to t

(c) 86.6. N/

bending msis of the rding to thτ is:9 5

g loads mus

ar stress the

is based ont. Venant's t

fail due to

pression is m

the correct eNOT the cor

s Differents the ma

heory of faermissible stress theo

(c) 2T

lar shaft uss theory

the permi

(c) 2 M

10- 6 m2 is se uniaxial

(c) 100 k

und to be 2pal stress ttorque will/mm2

moment of maximum he maximu

( )11 d 6

st be desig

ories

ntheory (d) Vo

o shear whe

more than h

explanation rrect explana

rence Taximum she

ailure, permtwisting m

ory of failur[IES-

under purof failure

issible ben

M

subjected tyield stres

N

S K Mo200 N/mm2. theory of fal be: [IES

(d) 100 N/m

400 kNm principal

um shear [IES

gned on the[IES

[IESon Mises the

en subjecte [IES

half its comp

of A ation of A

Theoryear stress t

[IES

missible twmoment wre will be: 1998: ISRO

(d) 2T

re bendinge. Accordi

nding mom[IES

(d) 2M

to a tensiless of the ma

[IES(d) 200 k

ondal’s Using

ailure, S-2000] mm2

and a stress stress

S-2000]

e basis S-1996]

S-1993] eory

d to a -2010]

pressive

y theory S-1999]

wisting ill the

O-2008]

g is M ing to

ment in S-1995]

e load. aterial S-2001] kN



IES-10. A cold roller steel shaft is designed on the basis of maximum shear stress theory. The principal stresses induced at its critical section are 60 MPa and - 60 MPa respectively. If the yield stress for the shaft material is 360 MPa, the factor of safety of the design is: [IES-2002]

(a) 2 (b) 3 (c) 4 (d) 6 IES-11. A shaft is subjected to a maximum bending stress of 80 N/mm2 and maximum

shearing stress equal to 30 N/mm2 at a particular section. If the yield point in tension of the material is 280 N/mm2, and the maximum shear stress theory of failure is used, then the factor of safety obtained will be: [IES-1994]

(a) 2.5 (b) 2.8 (c) 3.0 (d) 3.5 IES-12. For a two-dimensional state stress ( 1 2 1 2, 0, 0σ σ σ σ> > < ) the designed values

are most conservative if which one of the following failure theories were used? [IES-1998]

(a) Maximum principal strain theory (b) Maximum distortion energy theory (c) Maximum shear stress theory (d) Maximum principal stress theory

Shear Strain Energy Theory (Distortion energy theory) IES-13. Who postulated the maximum distortion energy theory? [IES-2008] (a) Tresca (b) Rankine (c) St. Venant (d) Mises-Henky IES-14. Who postulated the maximum distortion energy theory? [IES-2008] (a) Tresca (b) Rankine (c) St. Venant (d) Mises-Henky IES-15. The maximum distortion energy theory of failure is suitable to predict the

failure of which one of the following types of materials? [IES-2004] (a) Brittle materials (b) Ductile materials (c) Plastics (d) Composite materials IES-16. If σy is the yield strength of a particular material, then the distortion energy

theory is expressed as [IES-1994] (a) ( ) ( ) ( )2 2 2 2

1 2 2 3 3 1 2 yσ σ σ σ σ σ σ− + − + − =

(b) ( )2 2 2 21 2 3 1 2 2 3 3 12 ( ) yσ σ σ μ σ σ σ σ σ σ σ− + − + + =

(c) ( ) ( ) ( )2 2 2 21 2 2 3 3 1 3 yσ σ σ σ σ σ σ− + − + − =

(d) ( )( ) ( )2 21 2 31 2 2 1 yμ σ σ σ μ σ− + + = +

IES-17. If a shaft made from ductile material is subjected to combined bending and

twisting moments, calculations based on which one of the following failure theories would give the most conservative value? [IES-1996]

(a) Maximum principal stress theory (b) Maximum shear stress theory. (d Maximum strain energy theory (d) Maximum distortion energy theory.

Maximum Principal Strain Theory IES-18. Match List-I (Failure theories) with List-II (Figures representing boundaries of

these theories) and select the correct answer using the codes given below the Lists: [IES-1997]

List-I List-II A. Maximum principal stress

theory



B. Maximum shear stress theory

C. Maximum octahedral stress

theory

D. Maximum shear strain

energy theory



Maximum Principal Stress Theory IAS-1. For 1 2σ σ≠ and σ3 = 0, what is the physical boundary for Rankine failure

theory? [IAS-2004] (a) A rectangle (b) An ellipse (c) A square (d) A parabola

Shear Strain Energy Theory (Distortion energy theory) IAS-2. Consider the following statements: [IAS-2007]

1. Experiments have shown that the distortion-energy theory gives an accurate prediction about failure of a ductile component than any other theory of failure.

2. According to the distortion-energy theory, the yield strength in shear is less than the yield strength in tension.

Which of the statements given above is/are correct? (a) 1 only (b) 2 only (c) Both 1 and 2 (d) Neither 1 nor 2 IAS-3. Consider the following statements: [IAS-2003]

1. Distortion-energy theory is in better agreement for predicting the failure of ductile materials.

2. Maximum normal stress theory gives good prediction for the failure of brittle materials.

3. Module of elasticity in tension and compression are assumed to be different stress analysis of curved beams.

Which of these statements is/are correct? (a) 1, 2 and 3 (b) 1 and 2 (c) 3 only (d) 1 and 3 IAS-4. Which one of the following graphs represents Mises yield criterion? [IAS-

1996]



Maximum Principal Strain Theory IAS-5. Given that the principal stresses 1 2 3σ σ σ> > and σe is the elastic limit stress in

simple tension; which one of the following must be satisfied such that the elastic failure does not occur in accordance with the maximum principal strain theory? [IAS-2004]

(a) 31 2e

E E E Eσ σσ σμ μ⎛ ⎞< − −⎜ ⎟

⎝ ⎠ (b) 31 2e

E E E Eσ σσ σμ μ⎛ ⎞> − −⎜ ⎟

⎝ ⎠

(c) 31 2e

E E E Eσ σσ σμ μ⎛ ⎞> + +⎜ ⎟

⎝ ⎠ (d) 31 2e

E E E Eσ σσ σμ μ⎛ ⎞< + −⎜ ⎟

⎝ ⎠

OBJECTIVE ANSWERS

GATE-1. Ans. (a) - 3, (c) -1, (d) -5, (e) -2 St. Venant's law: Maximum principal strain theory GATE-2. Ans. (d) Aluminium is a ductile material so use maximum shear stress theory GATE-2(i) Ans. (b)

Shear stress = σ − σ1 2

2

∴ Shear stress = − =173 0 86.5 MPa2

GATE-3. Ans. (c)

( ) ( ) ( ){ }2 2 2s 1 2 2 3 3 1

1V Where E 2G(1 ) simplifyand get result.12G

σ σ σ σ σ σ μ= − + − + − = +

GATE-4. Ans. (c) According to distortion energy theory if maximum stress (σt) then

2 2 2t 1 2 1 2

2 2 2t

t

or

or 360 140 360 140or 314 MPa

σ σ σ σ σσσ

= + −

= + − ×=

GATE-5. Ans. (b)

( )

( ) ( ) ( ) ( ){ }( ) ( )( ) ( ) ( ){ }

( )

2 2 2 2 2 2

22 2 2

We know that equivalent stress

1 62

1 10 20 20 10 10 20 6 5 0 02

27.84

27.84Therefore Yield shear stress 16.073 3 3

e

x y y z z x xy yz zx

y ey

MPa

MPa

σ

σ σ σ σ σ σ τ τ τ

σ στ

= − + − + − + + +

= − + − − + − − + + +

=

= = = =

GATE-6. Ans. (c) IES-1. Ans. (d) IES-2. Ans. (d) For pure shear xτ σ=±



IES-3. Ans. (c) ( ) ( )2 2 2 23 3

16 16M M T and M Td d

σ τπ π

= + + = +

2 2 2 2

2 2 2 2

M M T 4 4 3 9Therefore5M T 4 3

στ

+ + + += = =+ +

IES-4. Ans. (a) IES-5. Ans. (b) Rankine's theory or maximum principle stress theory is most commonly used for

brittle materials. IES-5a Ans. (d) A cast iron specimen shall fail due to crushing when subjected to a compressive

load. A cast iron specimen shall fail due to tension when subjected to a tensile load. IES-6. Ans. (b)

IES-7. Ans. (d) yt3

16TGiven principalstresses for only thisshear stressare2dσ

τπ

= =

( )σ τ τ

σ σ σπ

= = ±

= =

21,2

1 2 yt 3

maximum principal stress theory of failuregives

16 2Tmax[ , ]

d

IES-8. Ans. (b) ( ) ( )2 2 2 23 3

16 16M M T and M Td d

σ τπ π

= + + = + put T = 0

3

ytyt 3 3 3

32M32M 16M 16Mdor and ThereforeM M

2 2d d dσ πσ τ

π π π

⎛ ⎞⎜ ⎟′ ⎝ ⎠ ′= = = = = =

IES-9. Ans. (b) Tresca failure criterion is maximum shear stress theory.

ytmax

P sin2 PWeknow that, orA 2 2A 2

σθτ τ= = = or ytP Aσ= ×

IES-10. Ans. (b)

IES-11. Ans. (b) Maximum shear stress = 2

2 280 0 30 50 N/mm2−⎛ ⎞ + =⎜ ⎟

⎝ ⎠

According to maximum shear stress theory,280; . . 2.8

2 2 50y F S

στ = ∴ = =

×

IES-12. Ans. (c)

Graphical comparison of different failure theories Above diagram shows that 1 20, 0σ σ> < will occur at 4th quadrant and most

conservative design will be maximum shear stress theory. IES-13. Ans. (d) IES-14. Ans. (d) Maximum shear stress theory → Tresca Maximum principal stress theory → Rankine Maximum principal strain theory → St. Venant Maximum shear strain energy theory → Mises – Henky



IES-15. Ans. (b) IES-16. Ans. (a) IES-17. Ans. (b)

IES-18. Ans. (d)

IAS IAS-1. Ans. (c) Rankine failure theory or

Maximum principle stress theory.

IAS-2. Ans. (c) 0.5773y

y y

στ σ= =

IAS-3. Ans. (b) IAS-4. Ans. (d) IAS-5. Ans. (b) Strain at yield point>principal strain

31 2e

E E E Eσ σσ σμ μ> − −


Conventional Question ESE-2010 Q. The stress state at a point in a body is plane with 2 2

1 2σ 60N / mm & σ 36N / mm= = − If the allowable stress for the material in simple tension or compression is 100 N/mm2 calculate the value of factor of safety with each of the following criteria for failure (i) Max Stress Criteria (ii) Max Shear Stress Criteria (iii) Max strain criteria (iv) Max Distortion energy criteria [10 Marks] Ans. The stress at a point in a body is plane



Allowable stress for the material in simple tension or compression is 100 N/mm2 Find out factor of safety for (i) Maximum stress Criteria : - In this failure point occurs when max principal stress

reaches the limiting strength of material. Therefore. Let F.S factor of safety

( )1

2

2

allowableF.S

100 N / mmF.S 1.67 Ans.60 N / mm

σσ =

= =

(ii) Maximum Shear stress criteria : - According to this failure point occurs at a point in a member when maximum shear stress reaches to shear at yield point

σγ = σ =

σ − σ +γ = = = =

=×

= = =×

=

yt 2max yt

21 2max

100 N / mm2 F.S

60 36 96 48 N / mm2 2 2

100482 F.S

100 100F.S 1.0422 48 96

F.S 1.042 Ans.

(iv) Maximum Distortion energy criteria ! – In this failure point occurs at a point in a member when distortion strain energy per unit volume in a bi – axial system reaches the limiting distortion strain energy at the of yield

( )

2yt2 2

1 2 1 2

222

F.S

10060 36 60 36F.S

F.S 1.19

σ⎛ ⎞σ + σ − σ ×σ = ⎜ ⎟

⎝ ⎠

⎛ ⎞+ −× × − = ⎜ ⎟⎝ ⎠

=

Conventional Question ESE-2006 Question: A mild steel shaft of 50 mm diameter is subjected to a beading moment of 1.5

kNm and torque T. If the yield point of steel in tension is 210 MPa, find the maximum value of the torque without causing yielding of the shaft material according to

(i) Maximum principal stress theory (ii) Maximum shear stress theory.

Answer: σπb 3

32We know that, Maximum bending stress ( ) Md

=

π 3

16and Maximum shear stress ( ) Td

τ =

σ σσ

π

22 2 2

1,2 3

Principal stresses are given by:

162 2

b b M M Td

τ⎛ ⎞ ⎡ ⎤⎟⎜= ± + = ± +⎟⎜ ⎢ ⎥⎟⎟⎜ ⎣ ⎦⎝ ⎠

2 21 260 N / mm 36 N / mmσ = σ = −



( )2 2 6

3

( ) According to Maximum principal stress theory

Maximum principal stress=Maximum stress at elastic limit

16 210 10

y

i

or M M Td

σ

π⎡ ⎤+ + = ×⎢ ⎥⎣ ⎦

( )2 2 6

3

16or 1500 1500 210 100.050

T = 3332 Nm = 3.332 kNm

T

or

π⎡ ⎤+ + = ×⎢ ⎥⎣ ⎦

1 2

1 2

σσ σ

σ σ σ

π

max

2 2 63

( ) According to Maximum shear stress theory

2 2,

16, 2× 210 10d

, T = 2096 N m = 2.096 kNm

y

y

ii

or

or M T

or

τ−

= =

− =

+ = ×

Conventional Question ESE-2005 Question: Illustrate the graphical comparison of following theories of failures for two-

dimensional stress system: (i) Maximum normal stress theory (ii) Maximum shear stress theory (iii) Distortion energy theory Answer:

Conventional Question ESE-2004 Question: State the Von- Mises's theory. Also give the naturally expression. Answer: According to this theory yielding would occur when total distortion energy absorbed

per unit volume due to applied loads exceeds the distortion energy absorbed per unit volume at the tensile yield point. The failure criterion is

( ) ( ) ( ) yσ σ σ σ σ σ σ2 2 2 21 2 2 3 3 1 2

[symbols has usual meaning]

− + − + − =


C

CQ

A

CQ

A

Chapter-15 ConventionQuestion:

Answer:

ConventionQuestion:

Answer:

nal QuestiDerive ansubjectedprincipal According per unit vovolume at change EV

Substitutin

At the tens

The failure

In a 2-D sit

nal Questi

A cube of (i) Dete(ii) Will

Von-Yield stren

ion ESE-2n expressiod to a unif

stress 3σ bto this theo

olume due tthe tensile can be given

ng strains in

sile yield poi

e criterion is

tuation if σ3

ion GATE-5mm side

ermine the the cube y

-Mises theongth of the m

Theorie2002 on for the form stresbeing zero.ory yieldingto applied loyield point. n as

n terms of st

int, σ1 = σy , σ

s thus obtain

= 0, the crit

-1996 is loaded aprincipal s

yield if theory. material etσ =

es of Failu

distortions state, gi.

g would occuoads exceedsTotal strain

tresses the d

σ2 = σ3 = 0 w

ned by equat

terion reduc

as shown instresses 1σe yield stre

= 70 MPa =

re

n energy peiven by th

ur when tots the distortn energy ET

distortion en

which gives

ting Ed and

ces to

n figure bel1 2 3,σ ,σ . ength of th

70 MN/m2 o

er unit volhe 1 2σ and σ

tal distortiontion energy and strain

nergy can be

Edy , which

low.

he material

or 70 N/mm2

S K Mo

lume for a2 with the

n energy ababsorbed penergy for v

given as

gives

l is 70 MPa

2.

ondal’s

a body third

bsorbed er unit volume

a? Use



( )

( )

( ) ( )

1 2 3

2 2

2 2

222

2 2

21

i Principal stress , , :2000 100080 N/mm ; 40 N/mm5 5 5 5500 80020 N/mm ; 32 N/mm5 5 5 5

80 40 80 40 322 2 2 2

60 20 32 97.74, 22.26

97.74N/mm , or 9

x y

z xy

x y x yxy

σ σ σ

σ σ

σ τ

σ σ σ σσ τ

σ

= = = =× ×

= = = =× ×

⎛ ⎞+ − ⎛ ⎞+ −⎟⎜ ⎟⎜⎟= ± + = ± +⎜ ⎟⎜⎟ ⎟⎜ ⎜⎟⎜ ⎝ ⎠⎝ ⎠

= ± + =

∴ =2

22

3

7.74 MPa

and 22.96N/mm or 22.96 MPa

20N/mm or 22 MPaz

σ

σ σ

=

= =

( )

( ) ( ) ( )

( ) ( ) ( )

( ) ( ) ( )( )

( ) ( )

2 2 2 21 2 2 3 3 1

2 2 21 2 2 3 3 1

2 2 2

22

ii Will thecube yieldor not?According to Von-Mises yield criteria, yielding will occur if

2

Now

97.74 22.96 22.96 20 20 97.74

11745.8

and, 2 2 70 9800

yt

yt

i

ii

σ σ σ σ σ σ σ

σ σ σ σ σ σ

σ

− + − + − ≥

− + − + −

= − + − + −

= −−−

= × = −−−

Since 11745.8 > 9800 so yielding will occur. Conventional Question GATE-1995 Question: A thin-walled circular tube of wall thickness t and mean radius r is subjected

to an axial load P and torque T in a combined tension-torsion experiment. (i) Determine the state of stress existing in the tube in terms of P and T. (ii) Using Von-Mises - Henky failure criteria show that failure takes place

when2 2

0 03 , ,.

where is the yield stress in uniaxial tensionand are respectively the axial and torsional stresses in the tubeσ τ σ σ

σ τ

+ =

Answer: Mean radius of the tube = r, Wall thickness of the tube = t, Axial load = P, and Torque = T. (i) The state of stress in the tube:

Due to axial load, the axial stress in the tube 2Px

rtσ

π=

Due to torque, shear stress,

( ){ }3 3

4 4 3 2

3

2 2

2 -neglecting t higher power of t.2

The state of stress in the tube is, , 0,2 2

xy

x y xy

Tr Tr TJ r t r t

J r t r r t

P Trt r t

τπ π

ππ

σ σ τπ π

= = =

= + − =

∴ = = =

(ii) Von Mises-Henky failure in tension for 2-dimensional stress is



2 2 20 1 2 1 2

22

1

22

2

2 2

2 2

x y x yxy

x y x yxy

σ σ σ σ σ

σ σ σ σσ τ

σ σ σ σσ τ

= + −

⎛ ⎞+ − ⎟⎜ ⎟= + +⎜ ⎟⎜ ⎟⎜⎝ ⎠

⎛ ⎞+ − ⎟⎜ ⎟= − +⎜ ⎟⎜ ⎟⎜⎝ ⎠

( )

22

1

22

2

2 2 22 2 2 2

2 2 2 2 20

In this case, , and2 4

02 4

2 4 2 4 2 4 2 4

x xxy

x xxy y

x x x x x x x xxy xy xy xy

σ σσ τ

σ σσ τ σ

σ σ σ σ σ σ σ σσ τ τ τ τ

= + +

= − + =

⎡ ⎤ ⎡ ⎤ ⎡ ⎤ ⎡ ⎤⎢ ⎥ ⎢ ⎥ ⎢ ⎥ ⎢ ⎥∴ = + + + − + − + + − +⎢ ⎥ ⎢ ⎥ ⎢ ⎥ ⎢ ⎥⎢ ⎥ ⎢ ⎥ ⎢ ⎥ ⎢ ⎥⎣ ⎦ ⎣ ⎦ ⎣ ⎦ ⎣ ⎦

∵

2 2 2 2 2 22 2 2 2

2 22

2 2

2 20

2. . 2. .4 4 2 4 4 4 2 4

4 4

3

3

x x x x x x x xxy xy xy xy

x xxy

x xy

x xy

σ σ σ σ σ σ σ στ τ τ τ

σ στ

σ τ

σ σ τ

⎡ ⎤ ⎡ ⎤⎢ ⎥ ⎢ ⎥= + + + + + + + + +⎢ ⎥ ⎢ ⎥⎢ ⎥ ⎢ ⎥⎣ ⎦ ⎣ ⎦⎡ ⎤⎢ ⎥− − −⎢ ⎥⎣ ⎦

= +

= +

Conventional Question GATE-1994 Question: Find the maximum principal stress developed in a cylindrical shaft. 8 cm in

diameter and subjected to a bending moment of 2.5 kNm and a twisting moment of 4.2 kNm. If the yield stress of the shaft material is 300 MPa. Determine the factor of safety of the shaft according to the maximum shearing stress theory of failure.

Answer: Given: d = 8 cm = 0.08 m; M = 2.5 kNm = 2500 Nm; T = 4.2 kNm = 4200 Nm

( )

( ) ( )

( )

2

2 22 2

36 2 2

max 3 3

2

300 300 MN/m

Equivalent torque, 2.5 4.2 4.888kNm

Maximum shear stress developed in the shaft,16 16 4.888 10 10 MN/m 48.62MN/m

0.08300Permissible shear stress 150MN/m

2

Fact

yield yt

e

MPa

T M T

Td

σ σ

τπ π

−

= =

= + = + =

× ×= = × =

×

= =

∴150or of safety 3.085

48.62= =


16.Th

Rive

heory a

eted

at a G

and

Glance

Weld

e (for I

ded J

IES, G

Joint

GATE, PSU)


Chapter-

-16

Rivetedd and Weldeed Joint S K Mondal’s


Chapter-16 Riveted and Welded Joint S K Mondal’s



Failure of riveted joint GATE-1. Bolts in the flanged end of pressure vessel are usually pre-tensioned Indicate

which of the following statements is NOT TRUE? [GATE-1999] (a) Pre-tensioning helps to seal the pressure vessel (b) Pre-tensioning increases the fatigue life of the bolts (c) Pre-tensioning reduces the maximum tensile stress in the bolts (d) Pre-tensioning helps to reduce the effect of pressure pulsations in the pressure vessel Statement for Linked Answers and Questions Q2 and Q3 A steel bar of 10 × 50 mm is cantilevered with two M 12 bolts (P and Q) to support a static load of 4 kN as shown in the figure.

GATE-2. The primary and secondary shear loads on bolt P, respectively, are: [GATE-2008]

(A) 2 kN, 20 kN (B) 20 kN, 2kN (C) 20kN,0kN (D) 0kN, 20 kN GATE-3. The resultant stress on bolt P is closest to [GATE-2008] (A) 132 MPa (B) 159 MPa (C) 178 MPa (D) 195 MPa GATE-3(i) Two threaded bolts A and B of same material and length are subjected to

identical tensile load. If the elastic strain energy stored in bolt A is 4 times that of bolt B and the mean diameter of bolt A is 12 mm, the mean diameter of bolt B in mm is [GATE-2013] (a) 16 (b) 24 (c) 36 (d) 48

GATE-4. A bolted joint is shown below. The maximum shear stress, in MPa, in the bolts

at A and B, respectively are: [GATE-2007]


Chapter-

GATE-5.

Commo

A fo

w3,

-16

(a) 242.6,

A brackerivet is 6

Direct sh(a) 4.4

on Data fosingle rive

ollowing ge

width of the, diameter o

42.5

et (shown i6 mm in dia

hear stress (b) 8.8

or Questieted lap joieometrical

e plate w = of the rivet

Riveted

(b) 42

in figure) iameter and

(in MPa) i8

ions GATint of two sand mater

200 mm, tht dr , = 10 m

d and Welde

25.5, 242.6

is rigidly md has an eff

in the most(c) 17.6

TE-5(i) ansimilar plaial details.

hickness ofmm, diamet

ed Joint

(c) 42

mounted onfective leng

t heavily lo(d

nd GATE-5tes as show

f the plate tter of the ri

.5, 42.5

n wall usingth of 12 m

oaded rivetd) 35.2

5(ii): wn in the fi

t = 5 mm, nivet hole d

S K

(d) 24

ng four rivemm. [GA

is:

igure below

number of r

h = 11 mm,

Mondal’s

42.6, 242.6

ets. Each ATE-2010]

w has the

rivets n =



allowable tensile stress of the plate σp = 200 MPa, allowable shear stress of the rivet σs, = 100 MPa and allowable bearing stress of the rivet σc, = 150 MPa.

GATE-5(i).If the rivets are to be designed to avoid crushing failure, the maximum

permissible load P in kN is [GATE-2013] (a) 7.50 (b) 1 5.00 (c) 22.50 (d) 30.00

GATE-5(ii). If the plates are to be designed to avoid tearing failure, the maximum

permissible load P in kN is [GATE-2013] (a) 83 (b) 125 (c) 167 (d) 501

Efficiency of a riveted joint GATE-6. If the ratio of the diameter of rivet hole to the pitch of rivets is 0.25, then the

tearing efficiency of the joint is: [GATE-1996] (a) 0.50 (b) 0.75 (c) 0.25 (d) 0.87 GATE-7. A manufacturer of rivets claims that the failure load in shear of his product is

500 ± 25 N. This specification implies that [GATE-1992] (a) No rivet is weaker than 475 N and stronger than 525 N (b) The standard deviation of strength of random sample of rivets is 25 N (c) There is an equal probability of failure strength to be either 475 Nor 525 N (d) There is approximately two-to-one chance that the strength of a rivet lies between

475 N to 525 N


Failure of riveted joint IES-1. An eccentrically loaded

riveted joint is shown with 4 rivets at P, Q, R and S.

Which of the rivets are the most loaded?

(a) P and Q (b) Q and R (c) Rand S (d) Sand P

[IES-2002]

IES-2. A riveted joint has been designed to

support an eccentric load P. The load generates value of F1 equal to 4 kN and F2 equal to 3 kN. The cross-sectional area of each rivet is 500 mm2. Consider the following statements:

1. The stress in the rivet is 10 N / mm2

2. The value of eccentricity L is 100 mm 3. The value of load P is 6 kN 4. The resultant force in each rivet is 6 kN Which of these statements are correct? (a) 1 and 2 (b) 2 and 3 (c) 3 and 4 (d) 1 and 3

[IES-2003]



IES-3. If permissible stress in plates of joint through a pin as shown in the given figure is 200 MPa, then the width w will be

(a) 15 mm (b) 18 mm (c) 20 mm (d) 25 mm

[IES-1999]

IES-4. For the bracket bolted as

shown in the figure, the bolts will develop

(a) Primary tensile stresses and secondary shear stresses

(b) Primary shear stresses and secondary shear stresses

(c) Primary shear stresses and secondary tensile stresses

(d) Primary tensile stresses and secondary compressive stresses

[IES-2000]IES-5. Assertion (A): In pre-loaded bolted joints, there is a tendency for failure to

occur in the gross plate section rather than through holes. [IES-2000] Reason (R): The effect of pre-loading is to create sufficient friction between the

assembled parts so that no slippage occurs. (a) Both A and R are individually true and R is the correct explanation of A (b) Both A and R are individually true but R is NOT the correct explanation of A (c) A is true but R is false (d) A is false but R is true IES-6. Two rigid plates are clamped by means of bolt and nut with an initial force N.

After tightening, a separating force P (P < N) is applied to the lower plate, which in turn acts on nut. The tension in the bolt after this is: [IES-1996]

(a) (N + P) (b) (N – P) (c) P (d) N

Efficiency of a riveted joint IES-7. Which one of the following structural joints with 10 rivets and same size of

plate and material will be the most efficient? [IES-1994]



IES-8. The most efficient riveted joint possible is one which would be as strong in

tension, shear and bearing as the original plates to be joined. But this can never be achieved because: [IES-1993]

(a) Rivets cannot be made with the same material (b) Rivets are weak in compression (c) There should be at least one hole in the plate reducing its strength (d) Clearance is present between the plate and the rivet

Advantages and disadvantages of welded joints IES-9. Assertion (A): In a boiler shell with riveted construction, the longitudinal scam

is, jointed by butt joint. [IES-2001] Reason (R): A butt joint is stronger than a lap joint in a riveted construction. (a) Both A and R are individually true and R is the correct explanation of A (b) Both A and R are individually true but R is NOT the correct explanation of A (c) A is true but R is false (d) A is false but R is true


Failure of riveted joint IAS-1. Two identical planks of

wood are connected by bolts at a pitch distance of 20 cm. The beam is subjected to a bending moment of 12 kNm, the shear force in the bolts will be:

(a) Zero (b) 0.1 kN (c) 0.2 kN (d) 4 kN

[IAS-2001]IAS-1. Ans. (a) IAS-2. Match List-I with List-II and select the correct answer using the code given

below the Lists: [IAS-2007] List-I List-II (Stress Induced) (Situation/ Location) A. Membrane stress 1. Neutral axis of beam B. Torsional shear stress 2. Closed coil helical spring under axial load C. Double shear stress 3. Cylindrical shell subject to fluid pressure D. Maximum shear stress 4. Rivets of double strap butt joint Code: A B C D A B C D (a) 3 1 4 2 (b) 4 2 3 1 (c) 3 2 4 1 (d) 4 1 3 2 IAS-2. Ans. (c)

OBJECTIVE ANSWERS

GATE-1. Ans. (c)

GATE-2. Ans. (a) Primary (Direct) Shear load = kkN 22

4 = N

GATE-3. Ans. (b)



GATE-3(i). Ans. (b) GATE-4. Ans. (a) GATE-5. Ans. (b)

2

1000 250250 N and 8.8MPa4 (6)

4π= = = = =FF z

A

GATE-5(i). Ans. (c) GATE-5(ii). Ans. (c) GATE-6. Ans. (b)

GATE-7. Ans. (a)

IES

IES-1. Ans. (b) IES-2. Ans. (d)

2

1 1 1

P = 2F = 2 x 3 = 6 kN and P.L = = 2 For 6 2 4 8

8or6

+= × =

=

Fl Fl lL l l

Ll

( ) ( )

2 21 2 1 2

2 2

Resultant force on rivet,

R = F +F +2FF cosθ

= 4 3 2 4 3cos

5kN

θ+ + × ×

=

32

Shear stresson rivet,R 5×10τ = =10 N/mm

Area 500

∴

=

IES-3. Ans. (a) (w – 10) × 2 × 10-6 × 200 × 106 = 2000 N; or w = 15 mm. IES-4. Ans. (a) IES-5. Ans. (a) IES-6. Ans. (a) IES-7. Ans. (b) IES-8. Ans. (c) Riveted joint can't be as strong as original plates, because there should be at least

one hole in the plate reducing its strength. IES-9. Ans. (c) IAS-1. Ans. (a) IAS-2. Ans. (c)




Conventional Question GATE-1994 Question: The longitudinal joint of a thin cylindrical pressure vessel, 6 m internal

diameter and 16 mm plate thickness, is double riveted lap point with no staggering between the rows. The rivets are of 20 mm nominal (diameter with a pitch of 72 mm. What is the efficiency of the joint and what would be the safe pressure inside the vessel? Allowable stresses for the plate and rivet materials are; 145 MN/m2 in shear and 230 MN/m2 in bearing. Take rivet hole diameter as 1.5 mm more than the rivet diameter.

Answer: Given: Diameter of rivet = 20 mm Diameter of hole = 20 + 1.5 = 21.5 mm Diameter the pressure vessel, d = 6 m Thickness of the plate, t = 16 mm Type of the joint: Double riveted lap joint Allowable stresses:

( )2 2 2

1

2

145 / ; 120 / ; 230 /72 2 21.5 16Strength of plate in tearing/pitch, 145

1000 10000.06728

20Strength of rivert in tearing/pitch, 2 1204 1000

0.0754

Strength of plate in crushin

c

t

s

MN m MN m MN m

R

MN

R

MN

σ τ σ

π

= = =⎡ ⎤− ×

= × ×⎢ ⎥⎢ ⎥⎣ ⎦

=

⎛ ⎞= × × ×⎜ ⎟⎝ ⎠

=20 16g/pitch, 2 230

1000 10000.1472 MN

sR ⎛ ⎞= × × ×⎜ ⎟⎝ ⎠

=

From the above three modes of failure it can be seen that the weakest element is the

plate as it will have tear failure at 0.06728 MN/pitch load itself. Stresses acting on the plate for an inside pressure of pN/m2 is shown in figure.

( )

( )

( )

6Hoop stress 187.52 2 0.016

6Longitudinal stress 93.754 4 0.016

Maximum principal stress acting on the plate2

only , .187.5 as there is no shear stress.

pd p pt

pd p pt

pdt

i e p

×= = =×

×= = =×

=



( ) ( )

( ) ( )

2

int

0.06728or 187.5 14572 2 21.5

0.0161000

or 0.7733 / 0.77330.06728 0.4028 40.28%

. . 0.072 0.016 145t

jot

p

p MN m or MPaR

p tη

σ

≤ ≤⎡ ⎤− ×

× ⎢ ⎥⎣ ⎦

≤

= = = =× ×

Conventional Question GATE-1995 Question: Determine the shaft diameter and bolt size for a marine flange-coupling

transmitting 3.75 MW at 150 r.p.m. The allowable shear stress in the shaft and bolts may be taken as 50 MPa. The number of bolts may be taken as 10 and bolt pitch circle diameter as 1.6 times the shaft diameter.

Answer: Given, P = 3.75MW; N = 150 r.p.m.;

6

6

3

6 3

6

50 ; 10, 1.6Shaft diameter, :

260

2 1503.78 1060

3.75 10 60or 238732 Nm2 150

Also,16

or 238732 50 1016

238732 16 0.28 290 mm50 10

Bolt size, :Bolt pitch circl

s b b

s

b

MPa n D DD

NTP

TE

T

T D

D

D m or

d

τ τ

π

π

ππτ

π

π

= = = =

=

× ×× =

× ×= =×

= × ×

= × ×

×⎛ ⎞∴ = =⎜ ⎟× ×⎝ ⎠

2

2 6

e diameter, 1.6 1.6 0.29 0.464m

Now,4 2

0.464or 238732 10 50 104 2

or 0.0512 m or 51.2 mm

b

bb b

b

b

D DDT n d

d

d

π τ

π

= = × =⎛ ⎞= × × × ⎜ ⎟⎝ ⎠

⎛ ⎞= × × × × ⎜ ⎟⎝ ⎠

=


SOM 2014 Bhopal

Documents

engineering stress

strain chapter

bending stress

shear stress

normal stress

principal stress

conventional stress

tensile stress distribution